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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 0.600 0.00 669.80 2.1162E+03 518.670 4.2409E+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 0.008 -0.095 0.0284 -0.096 -0.002 -0.297 2.860E-02 -1.087E-02 2.657E-05 1.235E-05 4.380E-04
-4.0 0.005 -0.034 0.0079 -0.034 0.003 -0.229 2.985E-02 -1.049E-02 2.885E-06 1.537E-06 1.570E-04
-2.0 0.005 0.024 -0.0136 0.024 0.006 -0.571 2.973E-02 -1.151E-02 2.423E-06 8.838E-07 -1.104E-04
0.0 0.007 0.085 -0.0381 0.085 0.007 -0.450 3.118E-02 -1.312E-02 2.514E-05 1.044E-05 -3.892E-04
2.0 0.011 0.149 -0.0661 0.149 0.006 -0.444 3.271E-02 -1.471E-02 7.506E-05 3.210E-05 -6.834E-04
4.0 0.018 0.216 -0.0970 0.216 0.003 -0.448 3.389E-02 -1.570E-02 1.557E-04 6.753E-05 -9.902E-04
8.0 0.039 0.355 -0.1620 0.357 -0.011 -0.454 3.352E-02 -1.661E-02 4.192E-04 1.836E-04 -1.631E-03
12.0 0.068 0.484 -0.2298 0.487 -0.034 -0.472 2.856E-02 -1.649E-02 7.859E-04 3.434E-04 -2.222E-03
16.0 0.097 0.584 -0.2939 0.588 -0.068 -0.500 2.022E-02 -1.459E-02 1.165E-03 5.059E-04 -2.681E-03
20.0 0.117 0.645 -0.3466 0.647 -0.111 -0.536 1.021E-02 -1.122E-02 1.466E-03 6.284E-04 -2.965E-03
24.0 0.124 0.665 -0.3836 0.658 -0.157 -0.583 -3.430E-04 -7.327E-03 1.609E-03 6.804E-04 -3.056E-03
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)= 1.00000E-05 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)= 6.02050E+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 0.900 2000.00 997.76 1.9677E+03 511.538 6.0205E+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 0.005 NDM NDM NDM NDM -0.440 2.908E-02 -1.279E-02 NDM NDM NDM
-4.0 NDM
-2.0 NDM
0.0 NDM
2.0 NDM
4.0 NDM
8.0 NDM
12.0 NDM
16.0 NDM
20.0 NDM
24.0 NDM
0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
CONFIGURATION AUXILIARY AND PARTIAL OUTPUT
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 0.900 2000.00 997.76 1.9677E+03 511.538 6.0205E+06 8.050 2.460 4.280 4.140 0.000
XCG RELATIVE TO THEORETICAL LEADING EDGE MAC= -0.36
BASIC PLANFORM PROPERTIES
TAPER ASPECT QUARTER CHORD QUARTER CHORD ZERO LIFT FRICTION
AREA RATIO RATIO SWEEP MAC X(MAC) Y(MAC) DRAG COEFFICIENT
0 WING
TOTAL THEORITICAL
+ 0.5629E+01 0.221 0.1797E+01 47.012 0.201E+01 0.501E+01 0.626E+00
TOTAL EXPOSED
+ 0.5629E+01 0.221 0.1797E+01 47.012 0.201E+01 0.501E+01 0.626E+00 0.459E-02 0.283E-02
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
CONFIGURATION AUXILIARY AND PARTIAL OUTPUT
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 0.900 2000.00 997.76 1.9677E+03 511.538 6.0205E+06 8.050 2.460 4.280 4.140 0.000
*** WING DATA FAIRING ***
CDL/CL**2 = 0.3584E+00 CLB/CL =-0.4011E-02
FORCE BREAK MACH NUMBER (ZERO SWEEP) = 0.9474E+00 FORCE BREAK MACH NUMBER (WITH SWEEP) = 0.9620E+00
MACH(A) = 1.032 CLA(A) = 0.2491E-01 MACH(B) = 1.102 CLA(B) = 0.2377E-01
(CLB/CL)M=0.6 =-0.4594E-02 (CLB/CL)M=1.4 =-0.2359E-02
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