WIP on 747 DATCOM, W+B complete.
This commit is contained in:
parent
b93ef5390e
commit
8ecc2a8b4b
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@ -5,7 +5,7 @@
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NALPHA = 20.,
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NALPHA = 20.,
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ALSCHD = -16., -12., -10., -8., -6., -4., -2., 0., 2., 4.,
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ALSCHD = -16., -12., -10., -8., -6., -4., -2., 0., 2., 4.,
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6., 8., 10., 12., 14., 16., 20., 24., 28., 32.,
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6., 8., 10., 12., 14., 16., 20., 24., 28., 32.,
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WT = 40000.,
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WT = 600000.,
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TR = 1.0,
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TR = 1.0,
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$END
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$END
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$OPTINS
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$OPTINS
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@ -15,27 +15,28 @@
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ROUGFC = 0.4E-3,
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ROUGFC = 0.4E-3,
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$END
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$END
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$SYNTHS
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$SYNTHS
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XCG = 1339.91,
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XCG = 1333.35,
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ZCG = 190.8,
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ZCG = 190.8,
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XW = 74.75,
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XW = 779.2,
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ZW = 0.,
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ZW = 150.0,
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ALIW = 0.,
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ALIW = 2.,
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$END
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$END
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$BODY
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$BODY
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NX = 20.,
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NX = 20.,
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X = 90.0, 125.0, 150.0, 200.0, 250.0, 300.0, 400.0, 600.0, 900.0, 1000.0,
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X = 90.0, 125.0, 150.0, 200.0, 250.0, 300.0, 400.0, 600.0, 900.0, 1000.0,
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1300.0, 1500.0, 1700.0, 1900.0, 2100.0, 2300.0, 2500.0, 2600.0, 2700.0,
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1300.0, 1500.0, 1700.0, 1900.0, 2100.0, 2300.0, 2500.0, 2600.0, 2700.0,
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2850.0
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2850.0,
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S = 0, 19453, 28953, 45683, 62025, 82328, 107506, 132497, 131740, 129847,
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S = 0., 19453., 28953., 45683., 62025., 82328., 107506., 132497., 131740.,
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115461, 122970, 123571, 124171, 107949, 80931, 56114, 46451, 36340, 0
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129847., 115461., 122970., 123571., 124171., 107949., 80931., 56114.,
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46451., 36340., 0.,
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R = 0.0, 36.0, 48.0, 63.5, 75.5, 85.5, 100.5, 120.5, 120.5, 120.5, 120.5,
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R = 0.0, 36.0, 48.0, 63.5, 75.5, 85.5, 100.5, 120.5, 120.5, 120.5, 120.5,
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127.5, 127.5, 127.5, 115.5, 92.5, 69.5, 59.5, 48.5, 0.0
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127.5, 127.5, 127.5, 115.5, 92.5, 69.5, 59.5, 48.5, 0.0,
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P = 0, 78.7, 96.0, 120.6, 140.5, 161.9, 185.0, 205.4, 204.8, 203.3, 191.7,
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P = 0., 78.7, 96.0, 120.6, 140.5, 161.9, 185.0, 205.4, 204.8, 203.3, 191.7,
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197.8, 198.3, 198.8, 185.4, 160.5, 133.6, 121.6, 107.6, 0
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197.8, 198.3, 198.8, 185.4, 160.5, 133.6, 121.6, 107.6, 0.,
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ZU = 230.0, 269.0, 282.0, 308.0, 331.0, 370.0, 395.0, 396.0, 393.0, 388.0,
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ZU = 230.0, 269.0, 282.0, 308.0, 331.0, 370.0, 395.0, 396.0, 393.0, 388.0,
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350.0, 349.0, 353.0, 357.0, 364.0, 372.0, 375.0, 378.0, 380.0, 340.0
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350.0, 349.0, 353.0, 357.0, 364.0, 372.0, 375.0, 378.0, 380.0, 340.0,
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ZL = 230.0, 194.0, 180.0, 158.0, 139.0, 127.0, 109.0, 92.0, 90.0, 90.0,
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ZL = 230.0, 194.0, 180.0, 158.0, 139.0, 127.0, 109.0, 92.0, 90.0, 90.0,
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90.0, 84.0, 89.0, 94.0, 133.0, 187.0, 236.0, 259.0, 283.0, 340.0
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90.0, 84.0, 89.0, 94.0, 133.0, 187.0, 236.0, 259.0, 283.0, 340.0,
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BNOSE = 2.,
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BNOSE = 2.,
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BTAIL = 2.,
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BTAIL = 2.,
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BLN = 275.,
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BLN = 275.,
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@ -45,20 +46,32 @@
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METHOD = 2.0,
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METHOD = 2.0,
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$END
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$END
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$WGPLNF
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$WGPLNF
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CHRDR = 292.,
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CHRDR = 665.,
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CHRDBP = 153.,
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CHRDBP = 362.,
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CHRDTP = 59.,
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CHRDTP = 121.,
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SSPN = 318.,
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SSPN = 1286.,
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SSPNE = 284.,
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SSPNE = 1158.,
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SSPNOP = 239.,
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SSPNOP = 775.,
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CHSTAT = 0.25,
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CHSTAT = 0.25,
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SAVSI = 39.75,
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SAVSI = 37.5,
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SAVSO = 26.,
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SAVSO = 37.5,
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TWISTA = 0.,
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TWISTA = 0.,
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SSPNDD = 238.,
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SSPNDD = 769.,
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DHDADI = -0.3,
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DHDADI = 7.0,
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TYPE = 3.0
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TYPE = 3.0,
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$END
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$END
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DIM IN
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DIM IN
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NACA-W-6-64A007
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SAVE
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CASEID BOEING 747-422
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NACA-W-6-642A414
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CASEID BOEING 747-422 CRANKED WING ONLY
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NEXT CASE
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$WGPLNF
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CHRDR = 601.,
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CHRDTP = 98.,
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CHSTAT = 0.25,
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SAVSI = 37.5,
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TWISTA = 0.,
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DHDADI = 7.0,
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TYPE = 3.0,
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$END
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CASEID BOEING 747-422 STRAIGHT TAPERED WING ONLY
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813
mfs/datcom/datcom.out
Normal file
813
mfs/datcom/datcom.out
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@ -0,0 +1,813 @@
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****************************************************
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* USAF STABILITY AND CONTROL DIGITAL DATCOM *
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* PROGRAM REV. JAN 96 DIRECT INQUIRIES TO: *
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* WRIGHT LABORATORY (WL/FIGC) ATTN: W. BLAKE *
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* WRIGHT PATTERSON AFB, OHIO 45433 *
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* PHONE (513) 255-6764, FAX (513) 258-4054 *
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****************************************************
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1 CONERR - INPUT ERROR CHECKING
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0 ERROR CODES - N* DENOTES THE NUMBER OF OCCURENCES OF EACH ERROR
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0 A - UNKNOWN VARIABLE NAME
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0 B - MISSING EQUAL SIGN FOLLOWING VARIABLE NAME
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0 C - NON-ARRAY VARIABLE HAS AN ARRAY ELEMENT DESIGNATION - (N)
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0 D - NON-ARRAY VARIABLE HAS MULTIPLE VALUES ASSIGNED
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0 E - ASSIGNED VALUES EXCEED ARRAY DIMENSION
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0 F - SYNTAX ERROR
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0****************************** INPUT DATA CARDS ******************************
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$FLTCON
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NMACH = 8.,
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MACH = 0.3, 0.6, 0.7, 0.75, 0.8, 0.86, 0.92, 0.95,
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ALT = 0.0,
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NALPHA = 20.,
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ALSCHD = -16., -12., -10., -8., -6., -4., -2., 0., 2., 4.,
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6., 8., 10., 12., 14., 16., 20., 24., 28., 32.,
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WT = 600000.,
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TR = 1.0,
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$END
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$OPTINS
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SREF = 815040.,
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CBARR = 327.78,
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BLREF = 2537.,
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ROUGFC = 0.4E-3,
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$END
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$SYNTHS
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XCG = 1333.35,
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ZCG = 190.8,
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XW = 779.2,
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ZW = 150.0,
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ALIW = 2.,
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$END
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$BODY
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NX = 20.,
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X = 90.0, 125.0, 150.0, 200.0, 250.0, 300.0, 400.0, 600.0, 900.0, 1000.0,
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1300.0, 1500.0, 1700.0, 1900.0, 2100.0, 2300.0, 2500.0, 2600.0, 2700.0,
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2850.0,
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S = 0., 19453., 28953., 45683., 62025., 82328., 107506., 132497., 131740.,
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129847., 115461., 122970., 123571., 124171., 107949., 80931., 56114.,
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46451., 36340., 0.,
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R = 0.0, 36.0, 48.0, 63.5, 75.5, 85.5, 100.5, 120.5, 120.5, 120.5, 120.5,
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127.5, 127.5, 127.5, 115.5, 92.5, 69.5, 59.5, 48.5, 0.0,
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P = 0., 78.7, 96.0, 120.6, 140.5, 161.9, 185.0, 205.4, 204.8, 203.3, 191.7,
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197.8, 198.3, 198.8, 185.4, 160.5, 133.6, 121.6, 107.6, 0.,
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ZU = 230.0, 269.0, 282.0, 308.0, 331.0, 370.0, 395.0, 396.0, 393.0, 388.0,
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350.0, 349.0, 353.0, 357.0, 364.0, 372.0, 375.0, 378.0, 380.0, 340.0,
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ZL = 230.0, 194.0, 180.0, 158.0, 139.0, 127.0, 109.0, 92.0, 90.0, 90.0,
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90.0, 84.0, 89.0, 94.0, 133.0, 187.0, 236.0, 259.0, 283.0, 340.0,
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BNOSE = 2.,
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BTAIL = 2.,
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BLN = 275.,
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BLA = 900.,
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DS = 57.,
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ITYPE = 2.,
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METHOD = 2.0,
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$END
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$WGPLNF
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|
CHRDR = 665.,
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CHRDBP = 362.,
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CHRDTP = 121.,
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SSPN = 1286.,
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SSPNE = 1158.,
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SSPNOP = 775.,
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CHSTAT = 0.25,
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SAVSI = 37.5,
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SAVSO = 37.5,
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TWISTA = 0.,
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SSPNDD = 769.,
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DHDADI = 7.0,
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TYPE = 3.0,
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$END
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DIM IN
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|
SAVE
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|
NACA-W-6-642A414
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|
CASEID BOEING 747-422 CRANKED WING ONLY
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NEXT CASE
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$WGPLNF
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|
CHRDR = 601.,
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CHRDTP = 98.,
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CHSTAT = 0.25,
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SAVSI = 37.5,
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TWISTA = 0.,
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DHDADI = 7.0,
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TYPE = 3.0,
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$END
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CASEID BOEING 747-422 STRAIGHT TAPERED WING ONLY
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1 THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE.
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|
0
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$FLTCON
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NMACH = 8.,
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MACH = 0.3, 0.6, 0.7, 0.75, 0.8, 0.86, 0.92, 0.95,
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ALT = 0.0,
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NALPHA = 20.,
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ALSCHD = -16., -12., -10., -8., -6., -4., -2., 0., 2., 4.,
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6., 8., 10., 12., 14., 16., 20., 24., 28., 32.,
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WT = 600000.,
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TR = 1.0,
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$END
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$OPTINS
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|
SREF = 815040.,
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|
CBARR = 327.78,
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BLREF = 2537.,
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|
ROUGFC = 0.4E-3,
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$END
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$SYNTHS
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|
XCG = 1333.35,
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|
ZCG = 190.8,
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|
XW = 779.2,
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ZW = 150.0,
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|
ALIW = 2.,
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$END
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$BODY
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|
NX = 20.,
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|
X = 90.0, 125.0, 150.0, 200.0, 250.0, 300.0, 400.0, 600.0, 900.0, 1000.0,
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1300.0, 1500.0, 1700.0, 1900.0, 2100.0, 2300.0, 2500.0, 2600.0, 2700.0,
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2850.0,
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|
S = 0., 19453., 28953., 45683., 62025., 82328., 107506., 132497., 131740.,
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129847., 115461., 122970., 123571., 124171., 107949., 80931., 56114.,
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46451., 36340., 0.,
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R = 0.0, 36.0, 48.0, 63.5, 75.5, 85.5, 100.5, 120.5, 120.5, 120.5, 120.5,
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127.5, 127.5, 127.5, 115.5, 92.5, 69.5, 59.5, 48.5, 0.0,
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|
P = 0., 78.7, 96.0, 120.6, 140.5, 161.9, 185.0, 205.4, 204.8, 203.3, 191.7,
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197.8, 198.3, 198.8, 185.4, 160.5, 133.6, 121.6, 107.6, 0.,
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|
ZU = 230.0, 269.0, 282.0, 308.0, 331.0, 370.0, 395.0, 396.0, 393.0, 388.0,
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|
350.0, 349.0, 353.0, 357.0, 364.0, 372.0, 375.0, 378.0, 380.0, 340.0,
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|
ZL = 230.0, 194.0, 180.0, 158.0, 139.0, 127.0, 109.0, 92.0, 90.0, 90.0,
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90.0, 84.0, 89.0, 94.0, 133.0, 187.0, 236.0, 259.0, 283.0, 340.0,
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BNOSE = 2.,
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BTAIL = 2.,
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BLN = 275.,
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BLA = 900.,
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DS = 57.,
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ITYPE = 2.,
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METHOD = 2.0,
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$END
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|
$WGPLNF
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|
CHRDR = 665.,
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CHRDBP = 362.,
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CHRDTP = 121.,
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SSPN = 1286.,
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SSPNE = 1158.,
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SSPNOP = 775.,
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CHSTAT = 0.25,
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SAVSI = 37.5,
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SAVSO = 37.5,
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TWISTA = 0.,
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|
SSPNDD = 769.,
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|
DHDADI = 7.0,
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||||||
|
TYPE = 3.0,
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|
$END
|
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|
DIM IN
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|
SAVE
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|
NACA-W-6-642A414
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|
CASEID BOEING 747-422 CRANKED WING ONLY
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NEXT CASE
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0 INPUT DIMENSIONS ARE IN IN, SCALE FACTOR IS 1.0000
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0*** WARNING *** WING NOT STRAIGHT TAPERED. UNIFORM SECTION ASSUMED.
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1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
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WING SECTION DEFINITION
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|
0 IDEAL ANGLE OF ATTACK = 0.00000 DEG.
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ZERO LIFT ANGLE OF ATTACK = -3.04952 DEG.
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IDEAL LIFT COEFFICIENT = 0.40000
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|
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ZERO LIFT PITCHING MOMENT COEFFICIENT = -0.08615
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MACH ZERO LIFT-CURVE-SLOPE = 0.09477 /DEG.
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|
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LEADING EDGE RADIUS = 0.01350 FRACTION CHORD
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|
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|
MAXIMUM AIRFOIL THICKNESS = 0.14000 FRACTION CHORD
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|
DELTA-Y = 2.87915 PERCENT CHORD
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|
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0 MACH= 0.3000 LIFT-CURVE-SLOPE = 0.09837 /DEG. XAC = 0.26812
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0 MACH= 0.6000 LIFT-CURVE-SLOPE = 0.11366 /DEG. XAC = 0.27338
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0 MACH= 0.7000 LIFT-CURVE-SLOPE = 0.12503 /DEG. XAC = 0.27674
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0 *** CREST CRITICAL MACH NUMBER EXCEEDED ***
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CREST CRITICAL MACH = 0.70775
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LOCATION = 0.46429 FRACTION CHORD
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|
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LIFT-CURVE-SLOPE = 0.10110 /DEG.
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|
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
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|
CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
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|
WING-BODY CONFIGURATION
|
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BOEING 747-422 CRANKED WING ONLY
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|
|
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----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------
|
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|
MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER
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|
NUMBER NUMBER AREA LONG. LAT. HORIZ VERT
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|
IN IN/SEC LB/IN**2 DEG R 1/FT IN**2 IN IN IN IN
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||||||
|
0 0.300 0.00 4018.77 1.4696E+01 518.670 2.1205E+06 ********* 327.780 2537.000 1333.350 190.800
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|
0 -------------------DERIVATIVE (PER DEGREE)-------------------
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|
0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB
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|
0
|
||||||
|
-16.0 0.170 -1.059 -0.1952 -1.065 -0.128 0.183 7.714E-02 4.846E-03 -4.366E-03 -2.211E-03 9.060E-03
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|
-12.0 0.064 -0.753 -0.1733 -0.750 -0.094 0.231 7.566E-02 6.143E-03 6.213E-03
|
||||||
|
-10.0 0.037 -0.603 -0.1603 -0.600 -0.068 0.267 7.487E-02 6.702E-03 4.811E-03
|
||||||
|
-8.0 0.028 -0.454 -0.1464 -0.453 -0.036 0.323 7.398E-02 7.575E-03 3.424E-03
|
||||||
|
-6.0 0.021 -0.307 -0.1300 -0.308 -0.011 0.423 7.302E-02 8.755E-03 2.055E-03
|
||||||
|
-4.0 0.017 -0.162 -0.1114 -0.163 0.006 0.685 7.202E-02 8.946E-03 7.038E-04
|
||||||
|
-2.0 0.015 -0.019 -0.0942 -0.019 0.015 4.844 7.097E-02 1.054E-02 -6.281E-04
|
||||||
|
0.0 0.016 0.122 -0.0693 0.122 0.016 -0.568 7.044E-02 1.183E-02 -1.940E-03
|
||||||
|
2.0 0.020 0.263 -0.0469 0.263 0.011 -0.178 5.868E-02 1.360E-02 -3.252E-03
|
||||||
|
4.0 0.024 0.357 -0.0148 0.357 -0.001 -0.042 3.859E-02 1.732E-02 -4.126E-03
|
||||||
|
6.0 0.027 0.417 0.0224 0.418 -0.017 0.054 3.091E-02 1.812E-02 -4.690E-03
|
||||||
|
8.0 0.030 0.480 0.0576 0.480 -0.037 0.120 3.216E-02 1.726E-02 -5.278E-03
|
||||||
|
10.0 0.035 0.546 0.0914 0.544 -0.061 0.168 3.357E-02 1.637E-02 -5.888E-03
|
||||||
|
12.0 0.040 0.615 0.1231 0.609 -0.089 0.202 3.484E-02 1.525E-02 -6.529E-03
|
||||||
|
14.0 0.049 0.685 0.1524 0.677 -0.118 0.225 3.503E-02 1.407E-02 -7.186E-03
|
||||||
|
16.0 0.063 0.755 0.1794 0.743 -0.148 0.242 3.486E-02 1.257E-02 -7.834E-03
|
||||||
|
20.0 0.124 0.895 0.2225 0.883 -0.190 0.252 3.465E-02 9.297E-03 -9.138E-03
|
||||||
|
24.0 0.195 1.032 0.2538 1.022 -0.241 0.248 3.376E-02 7.081E-03 -1.042E-02
|
||||||
|
28.0 0.185 1.165 0.2791 1.116 -0.383 0.250 3.244E-02 4.346E-03 -1.165E-02
|
||||||
|
32.0 0.178 1.291 0.2885 1.190 -0.533 0.243 3.087E-02 3.658E-04 -1.283E-02
|
||||||
|
0*** VEHICLE WEIGHT = 600000.00 LB.
|
||||||
|
0*** LEVEL FLIGHT LIFT COEFFICIENT = 0.79512
|
||||||
|
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
|
||||||
|
CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
|
||||||
|
WING-BODY CONFIGURATION
|
||||||
|
BOEING 747-422 CRANKED WING ONLY
|
||||||
|
|
||||||
|
----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------
|
||||||
|
MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER
|
||||||
|
NUMBER NUMBER AREA LONG. LAT. HORIZ VERT
|
||||||
|
IN IN/SEC LB/IN**2 DEG R 1/FT IN**2 IN IN IN IN
|
||||||
|
0 0.600 0.00 8037.55 1.4696E+01 518.670 4.2409E+06 ********* 327.780 2537.000 1333.350 190.800
|
||||||
|
0 -------------------DERIVATIVE (PER DEGREE)-------------------
|
||||||
|
0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB
|
||||||
|
0
|
||||||
|
-16.0 0.145 -1.136 -0.1666 -1.132 -0.173 0.147 8.254E-02 -1.285E-03 -4.366E-03 -2.350E-03 1.008E-02
|
||||||
|
-12.0 0.087 -0.809 -0.1607 -0.809 -0.083 0.199 8.106E-02 4.227E-03 6.945E-03
|
||||||
|
-10.0 0.040 -0.647 -0.1495 -0.644 -0.073 0.232 8.026E-02 5.224E-03 5.398E-03
|
||||||
|
-8.0 0.030 -0.488 -0.1398 -0.487 -0.038 0.287 7.937E-02 5.505E-03 3.868E-03
|
||||||
|
-6.0 0.022 -0.330 -0.1275 -0.330 -0.012 0.386 7.842E-02 6.727E-03 2.356E-03
|
||||||
|
-4.0 0.018 -0.174 -0.1129 -0.175 0.005 0.646 7.741E-02 6.840E-03 8.619E-04
|
||||||
|
-2.0 0.016 -0.020 -0.1001 -0.021 0.015 4.855 7.636E-02 8.574E-03 -6.120E-04
|
||||||
|
0.0 0.017 0.132 -0.0786 0.132 0.017 -0.597 7.583E-02 9.995E-03 -2.065E-03
|
||||||
|
2.0 0.021 0.283 -0.0601 0.284 0.011 -0.212 6.321E-02 1.204E-02 -3.519E-03
|
||||||
|
4.0 0.025 0.384 -0.0305 0.385 -0.002 -0.079 4.164E-02 1.635E-02 -4.489E-03
|
||||||
|
6.0 0.028 0.450 0.0053 0.450 -0.019 0.012 3.312E-02 1.739E-02 -5.115E-03
|
||||||
|
8.0 0.033 0.517 0.0391 0.516 -0.040 0.076 3.412E-02 1.654E-02 -5.758E-03
|
||||||
|
10.0 0.037 0.586 0.0714 0.584 -0.065 0.122 3.572E-02 1.554E-02 -6.423E-03
|
||||||
|
12.0 0.045 0.660 0.1012 0.655 -0.093 0.155 3.720E-02 1.423E-02 -7.128E-03
|
||||||
|
14.0 0.059 0.735 0.1283 0.728 -0.120 0.176 3.731E-02 1.280E-02 -7.849E-03
|
||||||
|
16.0 0.086 0.809 0.1524 0.801 -0.140 0.190 3.701E-02 1.120E-02 -8.558E-03
|
||||||
|
20.0 0.167 0.957 0.1905 0.957 -0.170 0.199 3.667E-02 8.902E-03 -9.980E-03
|
||||||
|
24.0 0.184 1.102 0.2236 1.082 -0.280 0.207 3.563E-02 6.951E-03 -1.137E-02
|
||||||
|
28.0 0.165 1.242 0.2461 1.175 -0.437 0.209 3.423E-02 3.005E-03 -1.271E-02
|
||||||
|
32.0 0.205 1.376 0.2477 1.276 -0.556 0.194 3.268E-02 -2.193E-03 -1.399E-02
|
||||||
|
0*** VEHICLE WEIGHT = 600000.00 LB.
|
||||||
|
0*** LEVEL FLIGHT LIFT COEFFICIENT = 0.19878
|
||||||
|
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
|
||||||
|
CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
|
||||||
|
WING-BODY CONFIGURATION
|
||||||
|
BOEING 747-422 CRANKED WING ONLY
|
||||||
|
|
||||||
|
----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------
|
||||||
|
MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER
|
||||||
|
NUMBER NUMBER AREA LONG. LAT. HORIZ VERT
|
||||||
|
IN IN/SEC LB/IN**2 DEG R 1/FT IN**2 IN IN IN IN
|
||||||
|
0 0.700 0.00 9377.14 1.4696E+01 518.670 4.9478E+06 ********* 327.780 2537.000 1333.350 190.800
|
||||||
|
0 -------------------DERIVATIVE (PER DEGREE)-------------------
|
||||||
|
0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB
|
||||||
|
0
|
||||||
|
-16.0 0.011 NDM NDM NDM NDM NDM NDM NDM -4.216E-03 -2.381E-03 NDM
|
||||||
|
-12.0 NDM
|
||||||
|
-10.0 NDM
|
||||||
|
-8.0 NDM
|
||||||
|
-6.0 NDM
|
||||||
|
-4.0 NDM
|
||||||
|
-2.0 NDM
|
||||||
|
0.0 NDM
|
||||||
|
2.0 NDM
|
||||||
|
4.0 NDM
|
||||||
|
6.0 NDM
|
||||||
|
8.0 NDM
|
||||||
|
10.0 NDM
|
||||||
|
12.0 NDM
|
||||||
|
14.0 NDM
|
||||||
|
16.0 NDM
|
||||||
|
20.0 NDM
|
||||||
|
24.0 NDM
|
||||||
|
28.0 NDM
|
||||||
|
32.0 NDM
|
||||||
|
0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST
|
||||||
|
0*** VEHICLE WEIGHT = 600000.00 LB.
|
||||||
|
0*** LEVEL FLIGHT LIFT COEFFICIENT = 0.14604
|
||||||
|
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
|
||||||
|
CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
|
||||||
|
WING-BODY CONFIGURATION
|
||||||
|
BOEING 747-422 CRANKED WING ONLY
|
||||||
|
|
||||||
|
----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------
|
||||||
|
MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER
|
||||||
|
NUMBER NUMBER AREA LONG. LAT. HORIZ VERT
|
||||||
|
IN IN/SEC LB/IN**2 DEG R 1/FT IN**2 IN IN IN IN
|
||||||
|
0 0.750 0.00 10046.93 1.4696E+01 518.670 5.3012E+06 ********* 327.780 2537.000 1333.350 190.800
|
||||||
|
0 -------------------DERIVATIVE (PER DEGREE)-------------------
|
||||||
|
0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB
|
||||||
|
0
|
||||||
|
-16.0 0.011 NDM NDM NDM NDM NDM NDM NDM -4.141E-03 -2.395E-03 NDM
|
||||||
|
-12.0 NDM
|
||||||
|
-10.0 NDM
|
||||||
|
-8.0 NDM
|
||||||
|
-6.0 NDM
|
||||||
|
-4.0 NDM
|
||||||
|
-2.0 NDM
|
||||||
|
0.0 NDM
|
||||||
|
2.0 NDM
|
||||||
|
4.0 NDM
|
||||||
|
6.0 NDM
|
||||||
|
8.0 NDM
|
||||||
|
10.0 NDM
|
||||||
|
12.0 NDM
|
||||||
|
14.0 NDM
|
||||||
|
16.0 NDM
|
||||||
|
20.0 NDM
|
||||||
|
24.0 NDM
|
||||||
|
28.0 NDM
|
||||||
|
32.0 NDM
|
||||||
|
0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST
|
||||||
|
0*** VEHICLE WEIGHT = 600000.00 LB.
|
||||||
|
0*** LEVEL FLIGHT LIFT COEFFICIENT = 0.12722
|
||||||
|
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
|
||||||
|
CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
|
||||||
|
WING-BODY CONFIGURATION
|
||||||
|
BOEING 747-422 CRANKED WING ONLY
|
||||||
|
|
||||||
|
----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------
|
||||||
|
MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER
|
||||||
|
NUMBER NUMBER AREA LONG. LAT. HORIZ VERT
|
||||||
|
IN IN/SEC LB/IN**2 DEG R 1/FT IN**2 IN IN IN IN
|
||||||
|
0 0.800 0.00 10716.73 1.4696E+01 518.670 5.6546E+06 ********* 327.780 2537.000 1333.350 190.800
|
||||||
|
0 -------------------DERIVATIVE (PER DEGREE)-------------------
|
||||||
|
0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB
|
||||||
|
0
|
||||||
|
-16.0 0.014 NDM NDM NDM NDM NDM NDM NDM -4.066E-03 -2.408E-03 NDM
|
||||||
|
-12.0 NDM
|
||||||
|
-10.0 NDM
|
||||||
|
-8.0 NDM
|
||||||
|
-6.0 NDM
|
||||||
|
-4.0 NDM
|
||||||
|
-2.0 NDM
|
||||||
|
0.0 NDM
|
||||||
|
2.0 NDM
|
||||||
|
4.0 NDM
|
||||||
|
6.0 NDM
|
||||||
|
8.0 NDM
|
||||||
|
10.0 NDM
|
||||||
|
12.0 NDM
|
||||||
|
14.0 NDM
|
||||||
|
16.0 NDM
|
||||||
|
20.0 NDM
|
||||||
|
24.0 NDM
|
||||||
|
28.0 NDM
|
||||||
|
32.0 NDM
|
||||||
|
0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST
|
||||||
|
0*** VEHICLE WEIGHT = 600000.00 LB.
|
||||||
|
0*** LEVEL FLIGHT LIFT COEFFICIENT = 0.11181
|
||||||
|
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
|
||||||
|
CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
|
||||||
|
WING-BODY CONFIGURATION
|
||||||
|
BOEING 747-422 CRANKED WING ONLY
|
||||||
|
|
||||||
|
----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------
|
||||||
|
MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER
|
||||||
|
NUMBER NUMBER AREA LONG. LAT. HORIZ VERT
|
||||||
|
IN IN/SEC LB/IN**2 DEG R 1/FT IN**2 IN IN IN IN
|
||||||
|
0 0.860 0.00 11520.48 1.4696E+01 518.670 6.0787E+06 ********* 327.780 2537.000 1333.350 190.800
|
||||||
|
0 -------------------DERIVATIVE (PER DEGREE)-------------------
|
||||||
|
0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB
|
||||||
|
0
|
||||||
|
-16.0 0.018 NDM NDM NDM NDM NDM NDM NDM -3.976E-03 -2.422E-03 NDM
|
||||||
|
-12.0 NDM
|
||||||
|
-10.0 NDM
|
||||||
|
-8.0 NDM
|
||||||
|
-6.0 NDM
|
||||||
|
-4.0 NDM
|
||||||
|
-2.0 NDM
|
||||||
|
0.0 NDM
|
||||||
|
2.0 NDM
|
||||||
|
4.0 NDM
|
||||||
|
6.0 NDM
|
||||||
|
8.0 NDM
|
||||||
|
10.0 NDM
|
||||||
|
12.0 NDM
|
||||||
|
14.0 NDM
|
||||||
|
16.0 NDM
|
||||||
|
20.0 NDM
|
||||||
|
24.0 NDM
|
||||||
|
28.0 NDM
|
||||||
|
32.0 NDM
|
||||||
|
0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST
|
||||||
|
0*** VEHICLE WEIGHT = 600000.00 LB.
|
||||||
|
0*** LEVEL FLIGHT LIFT COEFFICIENT = 0.09676
|
||||||
|
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
|
||||||
|
CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
|
||||||
|
WING-BODY CONFIGURATION
|
||||||
|
BOEING 747-422 CRANKED WING ONLY
|
||||||
|
|
||||||
|
----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------
|
||||||
|
MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER
|
||||||
|
NUMBER NUMBER AREA LONG. LAT. HORIZ VERT
|
||||||
|
IN IN/SEC LB/IN**2 DEG R 1/FT IN**2 IN IN IN IN
|
||||||
|
0 0.920 0.00 12324.24 1.4696E+01 518.670 6.5028E+06 ********* 327.780 2537.000 1333.350 190.800
|
||||||
|
0 -------------------DERIVATIVE (PER DEGREE)-------------------
|
||||||
|
0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB
|
||||||
|
0
|
||||||
|
-16.0 0.018 NDM NDM NDM NDM NDM NDM NDM -3.886E-03 -2.436E-03 NDM
|
||||||
|
-12.0 NDM
|
||||||
|
-10.0 NDM
|
||||||
|
-8.0 NDM
|
||||||
|
-6.0 NDM
|
||||||
|
-4.0 NDM
|
||||||
|
-2.0 NDM
|
||||||
|
0.0 NDM
|
||||||
|
2.0 NDM
|
||||||
|
4.0 NDM
|
||||||
|
6.0 NDM
|
||||||
|
8.0 NDM
|
||||||
|
10.0 NDM
|
||||||
|
12.0 NDM
|
||||||
|
14.0 NDM
|
||||||
|
16.0 NDM
|
||||||
|
20.0 NDM
|
||||||
|
24.0 NDM
|
||||||
|
28.0 NDM
|
||||||
|
32.0 NDM
|
||||||
|
0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST
|
||||||
|
0*** VEHICLE WEIGHT = 600000.00 LB.
|
||||||
|
0*** LEVEL FLIGHT LIFT COEFFICIENT = 0.08455
|
||||||
|
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
|
||||||
|
CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
|
||||||
|
WING-BODY CONFIGURATION
|
||||||
|
BOEING 747-422 CRANKED WING ONLY
|
||||||
|
|
||||||
|
----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------
|
||||||
|
MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER
|
||||||
|
NUMBER NUMBER AREA LONG. LAT. HORIZ VERT
|
||||||
|
IN IN/SEC LB/IN**2 DEG R 1/FT IN**2 IN IN IN IN
|
||||||
|
0 0.950 0.00 12726.11 1.4696E+01 518.670 6.7148E+06 ********* 327.780 2537.000 1333.350 190.800
|
||||||
|
0 -------------------DERIVATIVE (PER DEGREE)-------------------
|
||||||
|
0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB
|
||||||
|
0
|
||||||
|
-16.0 0.019 NDM NDM NDM NDM NDM NDM NDM -3.841E-03 -2.442E-03 NDM
|
||||||
|
-12.0 NDM
|
||||||
|
-10.0 NDM
|
||||||
|
-8.0 NDM
|
||||||
|
-6.0 NDM
|
||||||
|
-4.0 NDM
|
||||||
|
-2.0 NDM
|
||||||
|
0.0 NDM
|
||||||
|
2.0 NDM
|
||||||
|
4.0 NDM
|
||||||
|
6.0 NDM
|
||||||
|
8.0 NDM
|
||||||
|
10.0 NDM
|
||||||
|
12.0 NDM
|
||||||
|
14.0 NDM
|
||||||
|
16.0 NDM
|
||||||
|
20.0 NDM
|
||||||
|
24.0 NDM
|
||||||
|
28.0 NDM
|
||||||
|
32.0 NDM
|
||||||
|
0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST
|
||||||
|
0*** VEHICLE WEIGHT = 600000.00 LB.
|
||||||
|
0*** LEVEL FLIGHT LIFT COEFFICIENT = 0.07929
|
||||||
|
1 THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE.
|
||||||
|
0
|
||||||
|
$WGPLNF
|
||||||
|
CHRDR = 601.,
|
||||||
|
CHRDTP = 98.,
|
||||||
|
CHSTAT = 0.25,
|
||||||
|
SAVSI = 37.5,
|
||||||
|
TWISTA = 0.,
|
||||||
|
DHDADI = 7.0,
|
||||||
|
TYPE = 3.0,
|
||||||
|
$END
|
||||||
|
CASEID BOEING 747-422 STRAIGHT TAPERED WING ONLY
|
||||||
|
0 INPUT DIMENSIONS ARE IN IN, SCALE FACTOR IS 1.0000
|
||||||
|
|
||||||
|
0*** WARNING *** WING NOT STRAIGHT TAPERED. UNIFORM SECTION ASSUMED.
|
||||||
|
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
|
||||||
|
WING SECTION DEFINITION
|
||||||
|
0 IDEAL ANGLE OF ATTACK = 0.00000 DEG.
|
||||||
|
|
||||||
|
ZERO LIFT ANGLE OF ATTACK = -3.04952 DEG.
|
||||||
|
|
||||||
|
IDEAL LIFT COEFFICIENT = 0.40000
|
||||||
|
|
||||||
|
ZERO LIFT PITCHING MOMENT COEFFICIENT = -0.08615
|
||||||
|
|
||||||
|
MACH ZERO LIFT-CURVE-SLOPE = 0.09477 /DEG.
|
||||||
|
|
||||||
|
LEADING EDGE RADIUS = 0.01350 FRACTION CHORD
|
||||||
|
|
||||||
|
MAXIMUM AIRFOIL THICKNESS = 0.14000 FRACTION CHORD
|
||||||
|
|
||||||
|
DELTA-Y = 2.87915 PERCENT CHORD
|
||||||
|
|
||||||
|
|
||||||
|
0 MACH= 0.3000 LIFT-CURVE-SLOPE = 0.09837 /DEG. XAC = 0.26812
|
||||||
|
0 MACH= 0.6000 LIFT-CURVE-SLOPE = 0.11366 /DEG. XAC = 0.27338
|
||||||
|
0 MACH= 0.7000 LIFT-CURVE-SLOPE = 0.12503 /DEG. XAC = 0.27674
|
||||||
|
0 *** CREST CRITICAL MACH NUMBER EXCEEDED ***
|
||||||
|
|
||||||
|
CREST CRITICAL MACH = 0.70775
|
||||||
|
|
||||||
|
LOCATION = 0.46429 FRACTION CHORD
|
||||||
|
|
||||||
|
LIFT-CURVE-SLOPE = 0.10110 /DEG.
|
||||||
|
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
|
||||||
|
CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
|
||||||
|
WING-BODY CONFIGURATION
|
||||||
|
BOEING 747-422 STRAIGHT TAPERED WING ONLY
|
||||||
|
|
||||||
|
----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------
|
||||||
|
MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER
|
||||||
|
NUMBER NUMBER AREA LONG. LAT. HORIZ VERT
|
||||||
|
IN IN/SEC LB/IN**2 DEG R 1/FT IN**2 IN IN IN IN
|
||||||
|
0 0.300 0.00 4018.77 1.4696E+01 518.670 2.1205E+06 ********* 327.780 2537.000 1333.350 190.800
|
||||||
|
0 -------------------DERIVATIVE (PER DEGREE)-------------------
|
||||||
|
0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB
|
||||||
|
0
|
||||||
|
-16.0 0.180 -1.016 -0.2647 -1.026 -0.107 0.258 7.408E-02 1.131E-02 -4.372E-03 -2.211E-03 8.594E-03
|
||||||
|
-12.0 0.059 -0.722 -0.2194 -0.719 -0.093 0.305 7.260E-02 1.133E-02 5.884E-03
|
||||||
|
-10.0 0.036 -0.578 -0.1967 -0.575 -0.065 0.342 7.181E-02 1.163E-02 4.549E-03
|
||||||
|
-8.0 0.027 -0.435 -0.1729 -0.435 -0.034 0.398 7.092E-02 1.253E-02 3.230E-03
|
||||||
|
-6.0 0.021 -0.294 -0.1466 -0.295 -0.010 0.498 6.996E-02 1.366E-02 1.928E-03
|
||||||
|
-4.0 0.017 -0.155 -0.1182 -0.156 0.006 0.758 6.896E-02 1.404E-02 6.440E-04
|
||||||
|
-2.0 0.015 -0.018 -0.0904 -0.019 0.014 4.811 6.791E-02 1.538E-02 -6.208E-04
|
||||||
|
0.0 0.016 0.116 -0.0567 0.116 0.016 -0.487 6.738E-02 1.643E-02 -1.866E-03
|
||||||
|
2.0 0.020 0.251 -0.0247 0.252 0.011 -0.098 5.340E-02 1.783E-02 -3.111E-03
|
||||||
|
4.0 0.022 0.330 0.0146 0.331 -0.001 0.044 3.343E-02 2.005E-02 -3.839E-03
|
||||||
|
6.0 0.025 0.385 0.0555 0.385 -0.015 0.144 2.827E-02 2.008E-02 -4.347E-03
|
||||||
|
8.0 0.028 0.443 0.0949 0.443 -0.034 0.214 2.967E-02 1.934E-02 -4.884E-03
|
||||||
|
10.0 0.032 0.504 0.1329 0.502 -0.056 0.265 3.107E-02 1.853E-02 -5.443E-03
|
||||||
|
12.0 0.037 0.567 0.1690 0.563 -0.082 0.300 3.232E-02 1.757E-02 -6.033E-03
|
||||||
|
14.0 0.042 0.633 0.2032 0.624 -0.112 0.325 3.256E-02 1.647E-02 -6.638E-03
|
||||||
|
16.0 0.052 0.698 0.2349 0.685 -0.142 0.343 3.245E-02 1.506E-02 -7.236E-03
|
||||||
|
20.0 0.096 0.828 0.2888 0.811 -0.193 0.356 3.232E-02 1.179E-02 -8.442E-03
|
||||||
|
24.0 0.169 0.956 0.3292 0.942 -0.234 0.349 3.154E-02 8.980E-03 -9.625E-03
|
||||||
|
28.0 0.204 1.080 0.3606 1.050 -0.327 0.343 3.032E-02 6.494E-03 -1.077E-02
|
||||||
|
32.0 0.192 1.199 0.3812 1.119 -0.472 0.341 2.885E-02 3.779E-03 -1.187E-02
|
||||||
|
0*** VEHICLE WEIGHT = 600000.00 LB.
|
||||||
|
0*** LEVEL FLIGHT LIFT COEFFICIENT = 0.79512
|
||||||
|
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
|
||||||
|
CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
|
||||||
|
WING-BODY CONFIGURATION
|
||||||
|
BOEING 747-422 STRAIGHT TAPERED WING ONLY
|
||||||
|
|
||||||
|
----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------
|
||||||
|
MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER
|
||||||
|
NUMBER NUMBER AREA LONG. LAT. HORIZ VERT
|
||||||
|
IN IN/SEC LB/IN**2 DEG R 1/FT IN**2 IN IN IN IN
|
||||||
|
0 0.600 0.00 8037.55 1.4696E+01 518.670 4.2409E+06 ********* 327.780 2537.000 1333.350 190.800
|
||||||
|
0 -------------------DERIVATIVE (PER DEGREE)-------------------
|
||||||
|
0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB
|
||||||
|
0
|
||||||
|
-16.0 0.159 -1.086 -0.2441 -1.088 -0.147 0.224 7.905E-02 5.802E-03 -4.372E-03 -2.350E-03 9.549E-03
|
||||||
|
-12.0 0.083 -0.773 -0.2123 -0.773 -0.079 0.275 7.757E-02 1.011E-02 6.567E-03
|
||||||
|
-10.0 0.039 -0.619 -0.1899 -0.616 -0.069 0.308 7.677E-02 1.079E-02 5.098E-03
|
||||||
|
-8.0 0.029 -0.466 -0.1692 -0.465 -0.036 0.364 7.588E-02 1.102E-02 3.644E-03
|
||||||
|
-6.0 0.022 -0.315 -0.1459 -0.316 -0.011 0.462 7.493E-02 1.218E-02 2.209E-03
|
||||||
|
-4.0 0.017 -0.166 -0.1204 -0.167 0.006 0.721 7.392E-02 1.251E-02 7.917E-04
|
||||||
|
-2.0 0.016 -0.019 -0.0958 -0.020 0.015 4.823 7.287E-02 1.396E-02 -6.057E-04
|
||||||
|
0.0 0.017 0.125 -0.0646 0.125 0.017 -0.515 7.234E-02 1.511E-02 -1.983E-03
|
||||||
|
2.0 0.021 0.270 -0.0354 0.271 0.011 -0.131 5.737E-02 1.677E-02 -3.360E-03
|
||||||
|
4.0 0.024 0.355 0.0025 0.356 -0.001 0.007 3.598E-02 1.945E-02 -4.167E-03
|
||||||
|
6.0 0.027 0.414 0.0424 0.414 -0.017 0.102 3.019E-02 1.960E-02 -4.730E-03
|
||||||
|
8.0 0.030 0.476 0.0808 0.475 -0.036 0.170 3.139E-02 1.886E-02 -5.317E-03
|
||||||
|
10.0 0.035 0.539 0.1179 0.537 -0.060 0.219 3.294E-02 1.801E-02 -5.925E-03
|
||||||
|
12.0 0.040 0.607 0.1529 0.602 -0.087 0.254 3.439E-02 1.691E-02 -6.571E-03
|
||||||
|
14.0 0.049 0.677 0.1855 0.669 -0.116 0.277 3.456E-02 1.569E-02 -7.234E-03
|
||||||
|
16.0 0.065 0.746 0.2156 0.735 -0.143 0.294 3.433E-02 1.416E-02 -7.886E-03
|
||||||
|
20.0 0.135 0.883 0.2649 0.876 -0.176 0.302 3.410E-02 1.115E-02 -9.198E-03
|
||||||
|
24.0 0.192 1.018 0.3048 1.008 -0.239 0.302 3.318E-02 9.030E-03 -1.048E-02
|
||||||
|
28.0 0.186 1.149 0.3372 1.102 -0.375 0.306 3.191E-02 6.268E-03 -1.172E-02
|
||||||
|
32.0 0.170 1.274 0.3550 1.170 -0.531 0.303 3.049E-02 2.624E-03 -1.291E-02
|
||||||
|
0*** VEHICLE WEIGHT = 600000.00 LB.
|
||||||
|
0*** LEVEL FLIGHT LIFT COEFFICIENT = 0.19878
|
||||||
|
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
|
||||||
|
CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
|
||||||
|
WING-BODY CONFIGURATION
|
||||||
|
BOEING 747-422 STRAIGHT TAPERED WING ONLY
|
||||||
|
|
||||||
|
----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------
|
||||||
|
MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER
|
||||||
|
NUMBER NUMBER AREA LONG. LAT. HORIZ VERT
|
||||||
|
IN IN/SEC LB/IN**2 DEG R 1/FT IN**2 IN IN IN IN
|
||||||
|
0 0.700 0.00 9377.14 1.4696E+01 518.670 4.9478E+06 ********* 327.780 2537.000 1333.350 190.800
|
||||||
|
0 -------------------DERIVATIVE (PER DEGREE)-------------------
|
||||||
|
0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB
|
||||||
|
0
|
||||||
|
-16.0 0.011 NDM NDM NDM NDM NDM NDM NDM -4.222E-03 -2.381E-03 NDM
|
||||||
|
-12.0 NDM
|
||||||
|
-10.0 NDM
|
||||||
|
-8.0 NDM
|
||||||
|
-6.0 NDM
|
||||||
|
-4.0 NDM
|
||||||
|
-2.0 NDM
|
||||||
|
0.0 NDM
|
||||||
|
2.0 NDM
|
||||||
|
4.0 NDM
|
||||||
|
6.0 NDM
|
||||||
|
8.0 NDM
|
||||||
|
10.0 NDM
|
||||||
|
12.0 NDM
|
||||||
|
14.0 NDM
|
||||||
|
16.0 NDM
|
||||||
|
20.0 NDM
|
||||||
|
24.0 NDM
|
||||||
|
28.0 NDM
|
||||||
|
32.0 NDM
|
||||||
|
0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST
|
||||||
|
0*** VEHICLE WEIGHT = 600000.00 LB.
|
||||||
|
0*** LEVEL FLIGHT LIFT COEFFICIENT = 0.14604
|
||||||
|
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
|
||||||
|
CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
|
||||||
|
WING-BODY CONFIGURATION
|
||||||
|
BOEING 747-422 STRAIGHT TAPERED WING ONLY
|
||||||
|
|
||||||
|
----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------
|
||||||
|
MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER
|
||||||
|
NUMBER NUMBER AREA LONG. LAT. HORIZ VERT
|
||||||
|
IN IN/SEC LB/IN**2 DEG R 1/FT IN**2 IN IN IN IN
|
||||||
|
0 0.750 0.00 10046.93 1.4696E+01 518.670 5.3012E+06 ********* 327.780 2537.000 1333.350 190.800
|
||||||
|
0 -------------------DERIVATIVE (PER DEGREE)-------------------
|
||||||
|
0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB
|
||||||
|
0
|
||||||
|
-16.0 0.011 NDM NDM NDM NDM NDM NDM NDM -4.147E-03 -2.395E-03 NDM
|
||||||
|
-12.0 NDM
|
||||||
|
-10.0 NDM
|
||||||
|
-8.0 NDM
|
||||||
|
-6.0 NDM
|
||||||
|
-4.0 NDM
|
||||||
|
-2.0 NDM
|
||||||
|
0.0 NDM
|
||||||
|
2.0 NDM
|
||||||
|
4.0 NDM
|
||||||
|
6.0 NDM
|
||||||
|
8.0 NDM
|
||||||
|
10.0 NDM
|
||||||
|
12.0 NDM
|
||||||
|
14.0 NDM
|
||||||
|
16.0 NDM
|
||||||
|
20.0 NDM
|
||||||
|
24.0 NDM
|
||||||
|
28.0 NDM
|
||||||
|
32.0 NDM
|
||||||
|
0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST
|
||||||
|
0*** VEHICLE WEIGHT = 600000.00 LB.
|
||||||
|
0*** LEVEL FLIGHT LIFT COEFFICIENT = 0.12722
|
||||||
|
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
|
||||||
|
CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
|
||||||
|
WING-BODY CONFIGURATION
|
||||||
|
BOEING 747-422 STRAIGHT TAPERED WING ONLY
|
||||||
|
|
||||||
|
----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------
|
||||||
|
MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER
|
||||||
|
NUMBER NUMBER AREA LONG. LAT. HORIZ VERT
|
||||||
|
IN IN/SEC LB/IN**2 DEG R 1/FT IN**2 IN IN IN IN
|
||||||
|
0 0.800 0.00 10716.73 1.4696E+01 518.670 5.6546E+06 ********* 327.780 2537.000 1333.350 190.800
|
||||||
|
0 -------------------DERIVATIVE (PER DEGREE)-------------------
|
||||||
|
0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB
|
||||||
|
0
|
||||||
|
-16.0 0.014 NDM NDM NDM NDM NDM NDM NDM -4.072E-03 -2.408E-03 NDM
|
||||||
|
-12.0 NDM
|
||||||
|
-10.0 NDM
|
||||||
|
-8.0 NDM
|
||||||
|
-6.0 NDM
|
||||||
|
-4.0 NDM
|
||||||
|
-2.0 NDM
|
||||||
|
0.0 NDM
|
||||||
|
2.0 NDM
|
||||||
|
4.0 NDM
|
||||||
|
6.0 NDM
|
||||||
|
8.0 NDM
|
||||||
|
10.0 NDM
|
||||||
|
12.0 NDM
|
||||||
|
14.0 NDM
|
||||||
|
16.0 NDM
|
||||||
|
20.0 NDM
|
||||||
|
24.0 NDM
|
||||||
|
28.0 NDM
|
||||||
|
32.0 NDM
|
||||||
|
0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST
|
||||||
|
0*** VEHICLE WEIGHT = 600000.00 LB.
|
||||||
|
0*** LEVEL FLIGHT LIFT COEFFICIENT = 0.11181
|
||||||
|
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
|
||||||
|
CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
|
||||||
|
WING-BODY CONFIGURATION
|
||||||
|
BOEING 747-422 STRAIGHT TAPERED WING ONLY
|
||||||
|
|
||||||
|
----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------
|
||||||
|
MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER
|
||||||
|
NUMBER NUMBER AREA LONG. LAT. HORIZ VERT
|
||||||
|
IN IN/SEC LB/IN**2 DEG R 1/FT IN**2 IN IN IN IN
|
||||||
|
0 0.860 0.00 11520.48 1.4696E+01 518.670 6.0787E+06 ********* 327.780 2537.000 1333.350 190.800
|
||||||
|
0 -------------------DERIVATIVE (PER DEGREE)-------------------
|
||||||
|
0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB
|
||||||
|
0
|
||||||
|
-16.0 0.018 NDM NDM NDM NDM NDM NDM NDM -3.982E-03 -2.422E-03 NDM
|
||||||
|
-12.0 NDM
|
||||||
|
-10.0 NDM
|
||||||
|
-8.0 NDM
|
||||||
|
-6.0 NDM
|
||||||
|
-4.0 NDM
|
||||||
|
-2.0 NDM
|
||||||
|
0.0 NDM
|
||||||
|
2.0 NDM
|
||||||
|
4.0 NDM
|
||||||
|
6.0 NDM
|
||||||
|
8.0 NDM
|
||||||
|
10.0 NDM
|
||||||
|
12.0 NDM
|
||||||
|
14.0 NDM
|
||||||
|
16.0 NDM
|
||||||
|
20.0 NDM
|
||||||
|
24.0 NDM
|
||||||
|
28.0 NDM
|
||||||
|
32.0 NDM
|
||||||
|
0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST
|
||||||
|
0*** VEHICLE WEIGHT = 600000.00 LB.
|
||||||
|
0*** LEVEL FLIGHT LIFT COEFFICIENT = 0.09676
|
||||||
|
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
|
||||||
|
CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
|
||||||
|
WING-BODY CONFIGURATION
|
||||||
|
BOEING 747-422 STRAIGHT TAPERED WING ONLY
|
||||||
|
|
||||||
|
----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------
|
||||||
|
MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER
|
||||||
|
NUMBER NUMBER AREA LONG. LAT. HORIZ VERT
|
||||||
|
IN IN/SEC LB/IN**2 DEG R 1/FT IN**2 IN IN IN IN
|
||||||
|
0 0.920 0.00 12324.24 1.4696E+01 518.670 6.5028E+06 ********* 327.780 2537.000 1333.350 190.800
|
||||||
|
0 -------------------DERIVATIVE (PER DEGREE)-------------------
|
||||||
|
0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB
|
||||||
|
0
|
||||||
|
-16.0 0.018 NDM NDM NDM NDM NDM NDM NDM -3.892E-03 -2.436E-03 NDM
|
||||||
|
-12.0 NDM
|
||||||
|
-10.0 NDM
|
||||||
|
-8.0 NDM
|
||||||
|
-6.0 NDM
|
||||||
|
-4.0 NDM
|
||||||
|
-2.0 NDM
|
||||||
|
0.0 NDM
|
||||||
|
2.0 NDM
|
||||||
|
4.0 NDM
|
||||||
|
6.0 NDM
|
||||||
|
8.0 NDM
|
||||||
|
10.0 NDM
|
||||||
|
12.0 NDM
|
||||||
|
14.0 NDM
|
||||||
|
16.0 NDM
|
||||||
|
20.0 NDM
|
||||||
|
24.0 NDM
|
||||||
|
28.0 NDM
|
||||||
|
32.0 NDM
|
||||||
|
0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST
|
||||||
|
0*** VEHICLE WEIGHT = 600000.00 LB.
|
||||||
|
0*** LEVEL FLIGHT LIFT COEFFICIENT = 0.08455
|
||||||
|
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
|
||||||
|
CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
|
||||||
|
WING-BODY CONFIGURATION
|
||||||
|
BOEING 747-422 STRAIGHT TAPERED WING ONLY
|
||||||
|
|
||||||
|
----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------
|
||||||
|
MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER
|
||||||
|
NUMBER NUMBER AREA LONG. LAT. HORIZ VERT
|
||||||
|
IN IN/SEC LB/IN**2 DEG R 1/FT IN**2 IN IN IN IN
|
||||||
|
0 0.950 0.00 12726.11 1.4696E+01 518.670 6.7148E+06 ********* 327.780 2537.000 1333.350 190.800
|
||||||
|
0 -------------------DERIVATIVE (PER DEGREE)-------------------
|
||||||
|
0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB
|
||||||
|
0
|
||||||
|
-16.0 0.019 NDM NDM NDM NDM NDM NDM NDM -3.847E-03 -2.442E-03 NDM
|
||||||
|
-12.0 NDM
|
||||||
|
-10.0 NDM
|
||||||
|
-8.0 NDM
|
||||||
|
-6.0 NDM
|
||||||
|
-4.0 NDM
|
||||||
|
-2.0 NDM
|
||||||
|
0.0 NDM
|
||||||
|
2.0 NDM
|
||||||
|
4.0 NDM
|
||||||
|
6.0 NDM
|
||||||
|
8.0 NDM
|
||||||
|
10.0 NDM
|
||||||
|
12.0 NDM
|
||||||
|
14.0 NDM
|
||||||
|
16.0 NDM
|
||||||
|
20.0 NDM
|
||||||
|
24.0 NDM
|
||||||
|
28.0 NDM
|
||||||
|
32.0 NDM
|
||||||
|
0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST
|
||||||
|
0*** VEHICLE WEIGHT = 600000.00 LB.
|
||||||
|
0*** LEVEL FLIGHT LIFT COEFFICIENT = 0.07929
|
||||||
|
1 END OF JOB.
|
||||||
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