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LIFT-CURVE-SLOPE INTERPOLATION TABLE
MACH CL-ALPHA
0.750 0.2924E-01
0.962 0.2797E-01
1.032 0.2491E-01
1.102 0.2377E-01
1.400 0.2716E-01
1
A( 1)= 5.62860E+00 A( 2)= 1.28000E-30 A( 3)= 5.62860E+00 A( 4)= 5.62860E+00 A( 5)= 1.79661E+00
A( 6)= 1.00000E+00 A( 7)= 1.79661E+00 A( 8)= 1.00000E-30 A( 9)= 1.00000E-30 A( 10)= 2.90000E+00
A( 11)= 1.00000E-30 A( 12)= 1.00000E-30 A( 13)= 1.00000E-30 A( 14)= 1.00000E-30 A( 15)= 2.01047E+00
A( 16)= 2.01047E+00 A( 17)= 6.40000E-01 A( 18)= 7.83019E-01 A( 19)= 1.00000E+00 A( 20)= 1.00000E-30
A( 21)= 1.59000E+00 A( 22)= 1.00000E-30 A( 23)= 1.59000E+00 A( 24)= 1.00000E-30 A( 25)= 2.20690E-01
A( 26)= 2.20690E-01 A( 27)= 2.20690E-01 A( 28)= 1.00000E+00 A( 29)= 2.91076E+00 A( 30)= 1.89900E+00
A( 31)= 6.25819E-01 A( 32)= 6.25819E-01 A( 33)= 1.59000E+00 A( 34)= 5.50000E+01 A( 35)= 9.59931E-01
A( 36)= 8.19152E-01 A( 37)= 5.73576E-01 A( 38)= 1.42815E+00 A( 39)= 9.59931E-01 A( 40)= 4.70116E+01
A( 41)= 8.20506E-01 A( 42)= 7.31491E-01 A( 43)= 6.81851E-01 A( 44)= 1.07280E+00 A( 45)= 8.20506E-01
A( 46)= 3.56578E+01 A( 47)= 6.22346E-01 A( 48)= 5.82943E-01 A( 49)= 8.12513E-01 A( 50)= 7.17456E-01
A( 51)= 6.22346E-01 A( 52)= 3.87566E-01 A( 53)= 6.76431E-03 A( 54)= 6.76426E-03 A( 55)= 9.99977E-01
A( 56)= 6.76441E-03 A( 57)= 6.76431E-03 A( 58)= 5.50000E+01 A( 59)= 9.59931E-01 A( 60)= 8.19152E-01
A( 61)= 5.73576E-01 A( 62)= 1.42815E+00 A( 63)= 9.59931E-01 A( 64)= 4.70116E+01 A( 65)= 8.20506E-01
A( 66)= 7.31491E-01 A( 67)= 6.81851E-01 A( 68)= 1.07280E+00 A( 69)= 8.20506E-01 A( 70)= 3.56578E+01
A( 71)= 6.22346E-01 A( 72)= 5.82943E-01 A( 73)= 8.12513E-01 A( 74)= 7.17456E-01 A( 75)= 6.22346E-01
A( 76)= 3.87566E-01 A( 77)= 6.76431E-03 A( 78)= 6.76426E-03 A( 79)= 9.99977E-01 A( 80)= 6.76441E-03
A( 81)= 6.76431E-03 A( 82)= 0.00000E+00 A( 83)= 0.00000E+00 A( 84)= 0.00000E+00 A( 85)= 1.00000E+00
A( 86)= 0.00000E+00 A( 87)= 0.00000E+00 A( 88)= 0.00000E+00 A( 89)= 0.00000E+00 A( 90)= 0.00000E+00
A( 91)= 1.00000E+00 A( 92)= 0.00000E+00 A( 93)= 0.00000E+00 A( 94)= 0.00000E+00 A( 95)= 0.00000E+00
A( 96)= 0.00000E+00 A( 97)= 1.00000E+00 A( 98)= 0.00000E+00 A( 99)= 0.00000E+00 A(100)= 0.00000E+00
A(101)= 0.00000E+00 A(102)= 0.00000E+00 A(103)= 1.00000E+00 A(104)= 0.00000E+00 A(105)= 0.00000E+00
A(106)= 5.50000E+01 A(107)= 9.59931E-01 A(108)= 8.19152E-01 A(109)= 5.73576E-01 A(110)= 1.42815E+00
A(111)= 9.59931E-01 A(112)= 0.00000E+00 A(113)= 0.00000E+00 A(114)= 0.00000E+00 A(115)= 1.00000E+00
A(116)= 0.00000E+00 A(117)= 0.00000E+00 A(118)= 2.20690E-01 A(119)= 5.62860E+00 A(120)= 1.79661E+00
A(121)= 2.01047E+00 A(122)= 2.01047E+00 A(123)= 4.75379E-01 A(124)= 8.46243E-01 A(125)= 4.13593E+00
A(126)=-1.08652E+00 A(127)= 2.85598E+01 A(128)= 3.50000E+00 A(129)= 2.66828E+06 A(130)= 6.25819E-01
A(131)= 1.31250E-01 A(132)= 1.00000E-30 A(133)= 0.00000E+00 A(134)=-8.44619E-01 A(135)= 1.00000E-30
A(136)= 6.25819E-01 A(137)= 1.00000E+00 A(138)= 0.00000E+00 A(139)= 0.00000E+00 A(140)= 0.00000E+00
A(141)= 1.00000E+00 A(142)= 0.00000E+00 A(143)= 0.00000E+00 A(144)= 8.60750E+00 A(145)= 8.45000E-01
A(146)= 1.00000E-30 A(147)= 2.63547E+01 A(148)= 4.59976E-01 A(149)= 4.43927E-01 A(150)= 8.96063E-01
A(151)= 4.95419E-01 A(152)= 4.59976E-01 A(153)= 2.68382E+01 A(154)= 4.68415E-01 A(155)= 4.51473E-01
A(156)= 8.92285E-01 A(157)= 5.05974E-01 A(158)= 4.68415E-01 A(159)= 5.82759E-01 A(160)= 4.06108E+00
A(161)= 1.39638E+00 A(162)= 1.00000E+00 A(163)= 1.79661E+00 A(164)= 7.95000E-01 A(165)= 7.95000E-01
A(166)= 1.00000E-30 A(167)= 1.00000E-30 A(168)= 1.00000E-30 A(169)= 1.00000E-30 A(170)= 1.82759E-01
A(171)= 1.00000E-30 A(172)= 1.00000E-30 A(173)= 5.30000E-01 A(174)= 4.00000E-01 A(175)= 4.06822E+01
A(176)= 7.10038E-01 A(177)= 6.51863E-01 A(178)= 7.58337E-01 A(179)= 8.59595E-01 A(180)= 7.10038E-01
A(181)= 0.00000E+00 A(182)= 0.00000E+00 A(183)= 0.00000E+00 A(184)= 1.00000E+00 A(185)= 0.00000E+00
A(186)= 0.00000E+00 A(187)= 4.06822E+01 A(188)= 7.10038E-01 A(189)= 6.51863E-01 A(190)= 7.58337E-01
A(191)= 8.59595E-01 A(192)= 7.10038E-01 A(193)= 1.00000E-30 A(194)= 1.00000E-30 A(195)= 8.93762E-01
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
WING ALONE CONFIGURATION
STRAIGHT TAPERED EXPOSED WING SOLUTION, EXAMPLE PROBLEM 2, CASE 1
----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------
MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER
NUMBER NUMBER AREA LONG. LAT. HORIZ VERT
FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT
0 1.400 40000.00 1355.16 3.9312E+02 389.970 2.6683E+06 8.050 2.460 4.280 4.140 0.000
0 -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB
0
-6.0 0.021 -0.114 0.0542 -0.116 0.009 -0.468 2.716E-02 -1.356E-02 NDM NDM 2.702E-04
-4.0 0.016 -0.056 0.0271 -0.057 0.012 -0.477 2.862E-02 1.325E-04
-2.0 0.015 0.000 0.0000 -0.001 0.015 0.000 2.795E-02 1.187E-06
0.0 0.016 0.056 -0.0271 0.056 0.016 -0.485 2.862E-02 -1.302E-04
2.0 0.021 0.114 -0.0542 0.115 0.017 -0.471 2.978E-02 -2.681E-04
4.0 0.029 0.175 -0.0814 0.177 0.017 -0.461 3.052E-02 -4.113E-04
8.0 0.057 0.299 -0.1356 0.304 0.015 -0.446 3.088E-02 -7.082E-04
12.0 0.100 0.422 NDM 0.434 0.010 2.990E-02 -1.010E-03
16.0 0.153 0.538 NDM 0.560 -0.001 2.753E-02 -1.303E-03
20.0 0.212 0.642 NDM 0.676 -0.020 2.392E-02 -1.574E-03
24.0 0.269 0.730 NDM 0.776 -0.051 1.973E-02 -1.807E-03
0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST
A( 1)= 5.62860E+00 A( 2)= 1.28000E-30 A( 3)= 5.62860E+00 A( 4)= 5.62860E+00 A( 5)= 1.79661E+00
A( 6)= 1.00000E+00 A( 7)= 1.79661E+00 A( 8)= 1.00000E-30 A( 9)= 1.00000E-30 A( 10)= 2.90000E+00
A( 11)= 1.00000E-30 A( 12)= 1.00000E-30 A( 13)= 1.00000E-30 A( 14)= 1.00000E-30 A( 15)= 2.01047E+00
A( 16)= 2.01047E+00 A( 17)= 6.40000E-01 A( 18)= 7.83019E-01 A( 19)= 1.00000E+00 A( 20)= 1.00000E-30
A( 21)= 1.59000E+00 A( 22)= 1.00000E-30 A( 23)= 1.59000E+00 A( 24)= 1.00000E-30 A( 25)= 2.20690E-01
A( 26)= 2.20690E-01 A( 27)= 2.20690E-01 A( 28)= 1.00000E+00 A( 29)= 2.91076E+00 A( 30)= 1.89900E+00
A( 31)= 6.25819E-01 A( 32)= 6.25819E-01 A( 33)= 1.59000E+00 A( 34)= 5.50000E+01 A( 35)= 9.59931E-01
A( 36)= 8.19152E-01 A( 37)= 5.73576E-01 A( 38)= 1.42815E+00 A( 39)= 9.59931E-01 A( 40)= 4.70116E+01
A( 41)= 8.20506E-01 A( 42)= 7.31491E-01 A( 43)= 6.81851E-01 A( 44)= 1.07280E+00 A( 45)= 8.20506E-01
A( 46)= 3.56578E+01 A( 47)= 6.22346E-01 A( 48)= 5.82943E-01 A( 49)= 8.12513E-01 A( 50)= 7.17456E-01
A( 51)= 6.22346E-01 A( 52)= 3.87566E-01 A( 53)= 6.76431E-03 A( 54)= 6.76426E-03 A( 55)= 9.99977E-01
A( 56)= 6.76441E-03 A( 57)= 6.76431E-03 A( 58)= 5.50000E+01 A( 59)= 9.59931E-01 A( 60)= 8.19152E-01
A( 61)= 5.73576E-01 A( 62)= 1.42815E+00 A( 63)= 9.59931E-01 A( 64)= 4.70116E+01 A( 65)= 8.20506E-01
A( 66)= 7.31491E-01 A( 67)= 6.81851E-01 A( 68)= 1.07280E+00 A( 69)= 8.20506E-01 A( 70)= 3.56578E+01
A( 71)= 6.22346E-01 A( 72)= 5.82943E-01 A( 73)= 8.12513E-01 A( 74)= 7.17456E-01 A( 75)= 6.22346E-01
A( 76)= 3.87566E-01 A( 77)= 6.76431E-03 A( 78)= 6.76426E-03 A( 79)= 9.99977E-01 A( 80)= 6.76441E-03
A( 81)= 6.76431E-03 A( 82)= 0.00000E+00 A( 83)= 0.00000E+00 A( 84)= 0.00000E+00 A( 85)= 1.00000E+00
A( 86)= 0.00000E+00 A( 87)= 0.00000E+00 A( 88)= 0.00000E+00 A( 89)= 0.00000E+00 A( 90)= 0.00000E+00
A( 91)= 1.00000E+00 A( 92)= 0.00000E+00 A( 93)= 0.00000E+00 A( 94)= 0.00000E+00 A( 95)= 0.00000E+00
A( 96)= 0.00000E+00 A( 97)= 1.00000E+00 A( 98)= 0.00000E+00 A( 99)= 0.00000E+00 A(100)= 0.00000E+00
A(101)= 0.00000E+00 A(102)= 0.00000E+00 A(103)= 1.00000E+00 A(104)= 0.00000E+00 A(105)= 0.00000E+00
A(106)= 5.50000E+01 A(107)= 9.59931E-01 A(108)= 8.19152E-01 A(109)= 5.73576E-01 A(110)= 1.42815E+00
A(111)= 9.59931E-01 A(112)= 0.00000E+00 A(113)= 0.00000E+00 A(114)= 0.00000E+00 A(115)= 1.00000E+00
A(116)= 0.00000E+00 A(117)= 0.00000E+00 A(118)= 2.20690E-01 A(119)= 5.62860E+00 A(120)= 1.79661E+00
A(121)= 2.01047E+00 A(122)= 2.01047E+00 A(123)= 4.75379E-01 A(124)= 8.46243E-01 A(125)= 4.13593E+00
A(126)=-1.08652E+00 A(127)= 2.85598E+01 A(128)= 3.50000E+00 A(129)= 4.26444E+05 A(130)= 6.25819E-01
A(131)= 1.31250E-01 A(132)= 1.00000E-30 A(133)= 0.00000E+00 A(134)=-8.44619E-01 A(135)= 1.00000E-30
A(136)= 6.25819E-01 A(137)= 1.00000E+00 A(138)= 0.00000E+00 A(139)= 0.00000E+00 A(140)= 0.00000E+00
A(141)= 1.00000E+00 A(142)= 0.00000E+00 A(143)= 0.00000E+00 A(144)= 8.60750E+00 A(145)= 8.45000E-01
A(146)= 1.00000E-30 A(147)= 2.63547E+01 A(148)= 4.59976E-01 A(149)= 4.43927E-01 A(150)= 8.96063E-01
A(151)= 4.95419E-01 A(152)= 4.59976E-01 A(153)= 2.68382E+01 A(154)= 4.68415E-01 A(155)= 4.51473E-01
A(156)= 8.92285E-01 A(157)= 5.05974E-01 A(158)= 4.68415E-01 A(159)= 5.82759E-01 A(160)= 4.06108E+00
A(161)= 1.39638E+00 A(162)= 1.00000E+00 A(163)= 1.79661E+00 A(164)= 7.95000E-01 A(165)= 7.95000E-01
A(166)= 1.00000E-30 A(167)= 1.00000E-30 A(168)= 1.00000E-30 A(169)= 1.00000E-30 A(170)= 1.82759E-01
A(171)= 1.00000E-30 A(172)= 1.00000E-30 A(173)= 5.30000E-01 A(174)= 4.00000E-01 A(175)= 4.06822E+01
A(176)= 7.10038E-01 A(177)= 6.51863E-01 A(178)= 7.58337E-01 A(179)= 8.59595E-01 A(180)= 7.10038E-01
A(181)= 0.00000E+00 A(182)= 0.00000E+00 A(183)= 0.00000E+00 A(184)= 1.00000E+00 A(185)= 0.00000E+00
A(186)= 0.00000E+00 A(187)= 4.06822E+01 A(188)= 7.10038E-01 A(189)= 6.51863E-01 A(190)= 7.58337E-01
A(191)= 8.59595E-01 A(192)= 7.10038E-01 A(193)= 1.00000E-30 A(194)= 1.00000E-30 A(195)= 8.93762E-01
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
WING ALONE CONFIGURATION
STRAIGHT TAPERED EXPOSED WING SOLUTION, EXAMPLE PROBLEM 2, CASE 1
----------------------- FLIGHT CONDITIONS ------------------------ -------------- REFERENCE DIMENSIONS ------------
MACH ALTITUDE VELOCITY PRESSURE TEMPERATURE REYNOLDS REF. REFERENCE LENGTH MOMENT REF. CENTER
NUMBER NUMBER AREA LONG. LAT. HORIZ VERT
FT FT/SEC LB/FT**2 DEG R 1/FT FT**2 FT FT FT FT
0 2.500 90000.00 2460.43 3.6777E+01 403.136 4.2644E+05 8.050 2.460 4.280 4.140 0.000
0 -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB
0
-6.0 0.020 -0.070 0.0357 -0.072 0.012 -0.498 1.643E-02 -8.921E-03 NDM NDM 9.845E-05
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