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1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
WING-BODY CONFIGURATION
PLAIN FLAPS ON WING, EXAMPLE PROBLEM 5, CASE 2
----------------------- 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 4.2600E+06 2.250 0.822 3.000 2.600 0.000
0 -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA CD CL CM CN CA XCP CLA CMA CYB CNB CLB
0
-2.0 0.016 -0.125 0.0032 -0.126 0.012 -0.026 6.258E-02 -1.352E-03 -1.612E-03 -1.845E-03 5.509E-04
0.0 0.015 0.000 0.0000 0.000 0.015 ****** 6.258E-02 -1.864E-03 -5.244E-12
2.0 0.016 0.125 -0.0042 0.126 0.012 -0.034 6.273E-02 -2.646E-03 -5.509E-04
4.0 0.024 0.251 -0.0106 0.252 0.006 -0.042 6.269E-02 -3.674E-03 -1.104E-03
8.0 0.067 0.500 -0.0293 0.505 -0.003 -0.058 6.082E-02 -4.565E-03 -2.201E-03
12.0 0.149 0.738 -0.0471 0.752 -0.007 -0.063 5.089E-02 -3.125E-03 -3.246E-03
16.0 0.236 0.907 -0.0543 0.937 -0.023 -0.058 3.176E-02 -1.423E-03 -3.993E-03
20.0 0.992 -0.0585 9.201E-03 -1.326E-04 -4.364E-03
24.0 0.981 -0.0554 -1.458E-02 1.698E-03 -4.317E-03
FCM( 1)= 5.13402E+01 FCM( 2)= 5.17030E+00 FCM( 3)= 3.74516E+00 FCM( 4)= 2.65321E+00 FCM( 5)= 1.97316E+00
FCM( 6)= 6.96020E-01 FCM( 7)= 0.00000E+00 FCM( 8)= 1.40000E-01 FCM( 9)= 1.42300E-01 FCM( 10)= 2.81700E-01
FCM( 11)= 4.15300E-01 FCM( 12)= 4.72000E-01 FCM( 13)= 5.40700E-01 FCM( 14)= 6.54900E-01 FCM( 15)= 7.55700E-01
FCM( 16)= 8.41200E-01 FCM( 17)= 9.09700E-01 FCM( 18)= 9.59500E-01 FCM( 19)= 9.89800E-01 FCM( 20)= 1.00000E+00
FCM( 21)=-1.91186E-02 FCM( 22)=-2.34326E-02 FCM( 23)=-2.35110E-02 FCM( 24)=-2.81482E-02 FCM( 25)=-3.12759E-02
FCM( 26)=-3.00327E-02 FCM( 27)=-2.83284E-02 FCM( 28)=-2.24166E-02 FCM( 29)=-1.70821E-02 FCM( 30)=-1.33460E-02
FCM( 31)=-1.12025E-02 FCM( 32)=-6.07481E-03 FCM( 33)=-1.62185E-03 FCM( 34)= 0.00000E+00 FCM( 35)= 2.15990E-01
FCM( 36)= 1.76124E-01 FCM( 37)= 1.75469E-01 FCM( 38)= 1.26859E-01 FCM( 39)= 8.16610E-02 FCM( 40)= 7.12401E-02
FCM( 41)= 5.86138E-02 FCM( 42)= 4.53842E-02 FCM( 43)= 3.55929E-02 FCM( 44)= 2.77489E-02 FCM( 45)= 1.97555E-02
FCM( 46)= 9.63836E-03 FCM( 47)= 2.42745E-03 FCM( 48)= 0.00000E+00 FCM( 49)= 4.38054E-01 FCM( 50)= 4.22795E-01
FCM( 51)= 4.22544E-01 FCM( 52)= 3.92166E-01 FCM( 53)= 3.43968E-01 FCM( 54)= 3.09884E-01 FCM( 55)= 2.68587E-01
FCM( 56)= 1.91640E-01 FCM( 57)= 1.33660E-01 FCM( 58)= 9.54973E-02 FCM( 59)= 7.06577E-02 FCM( 60)= 3.48898E-02
FCM( 61)= 8.78708E-03 FCM( 62)= 0.00000E+00 FCM( 63)=-3.81781E-01 FCM( 64)=-3.81781E-01 FCM( 65)=-3.81781E-01
FCM( 66)=-3.81781E-01 FCM( 67)=-3.81781E-01 FCM( 68)=-3.81781E-01 FCM( 69)=-3.81781E-01 FCM( 70)= 1.00000E-30
FCM( 71)= 1.00000E-30 FCM( 72)= 1.00000E-30 FCM( 73)= 1.04604E+00 FCM( 74)= 9.48034E-01 FCM( 75)= 9.46424E-01
FCM( 76)= 8.48839E-01 FCM( 77)= 7.55313E-01 FCM( 78)= 7.15621E-01 FCM( 79)= 6.67528E-01 FCM( 80)= 5.87584E-01
FCM( 81)= 5.17020E-01 FCM( 82)= 4.57167E-01 FCM( 83)= 4.09214E-01 FCM( 84)= 3.74352E-01 FCM( 85)= 3.53141E-01
FCM( 86)= 3.46000E-01 FCM( 87)= 2.22064E-01 FCM( 88)= 2.46671E-01 FCM( 89)= 2.47075E-01 FCM( 90)= 2.65307E-01
FCM( 91)= 2.62307E-01 FCM( 92)= 2.38644E-01 FCM( 93)= 2.09974E-01 FCM( 94)= 1.46255E-01 FCM( 95)= 9.80668E-02
FCM( 96)= 6.77484E-02 FCM( 97)= 5.09022E-02 FCM( 98)= 2.52514E-02 FCM( 99)= 6.35963E-03 FCM(100)= 0.00000E+00
FCM(101)= 1.20000E-01 FCM(102)= 1.00000E-30 FCM(103)= 1.00000E-30 FCM(104)= 1.00000E-30 FCM(105)= 1.00000E-30
FCM(106)= 1.00000E-30 FCM(107)= 5.86700E-01 FCM(108)= 1.53900E-02 FCM(109)= 0.00000E+00 FCM(110)= 0.00000E+00
FCM(111)= 0.00000E+00 FCM(112)= 0.00000E+00 FCM(113)= 0.00000E+00 FCM(114)= 1.00000E-30 FCM(115)= 1.93849E+00
FCM(116)= 2.14359E+00 FCM(117)= 2.14696E+00 FCM(118)= 2.35118E+00 FCM(119)= 2.54691E+00 FCM(120)= 2.62997E+00
FCM(121)= 2.73062E+00 FCM(122)= 2.89792E+00 FCM(123)= 3.04560E+00 FCM(124)= 3.17086E+00 FCM(125)= 3.27121E+00
FCM(126)= 3.34417E+00 FCM(127)= 3.38856E+00 FCM(128)= 3.40350E+00 FCM(129)= 0.00000E+00 FCM(130)= 2.20878E-01
FCM(131)= 2.20859E-01 FCM(132)= 2.19538E-01 FCM(133)= 2.17952E-01 FCM(134)= 2.17154E-01 FCM(135)= 0.00000E+00
FCM(136)= 0.00000E+00 FCM(137)= 0.00000E+00 FCM(138)= 0.00000E+00 FCM(139)= 0.00000E+00 FCM(140)= 0.00000E+00
FCM(141)= 0.00000E+00 FCM(142)= 0.00000E+00 FCM(143)= 4.19601E-01 FCM(144)=-7.05109E-01 FCM(145)=-7.03743E-01
FCM(146)=-6.75253E-01 FCM(147)=-7.37081E-01 FCM(148)=-8.16211E-01 FCM(149)=-6.69546E-01 FCM(150)=-5.48248E-01
FCM(151)=-6.99334E-01 FCM(152)=-8.33513E-01 FCM(153)=-9.41013E-01 FCM(154)=-1.01917E+00 FCM(155)=-1.06672E+00
FCM(156)=-1.06672E+00 FCM(157)= 3.88070E-01 FCM(158)=-7.05109E-01 FCM(159)=-7.03743E-01 FCM(160)=-6.75253E-01
FCM(161)=-7.37081E-01 FCM(162)=-8.16210E-01 FCM(163)=-6.69546E-01 FCM(164)=-5.48248E-01 FCM(165)=-6.99334E-01
FCM(166)=-8.33513E-01 FCM(167)=-9.41013E-01 FCM(168)=-1.01917E+00 FCM(169)=-1.06672E+00 FCM(170)=-1.06672E+00
FCM(171)= 3.88071E-01 FCM(172)=-7.05107E-01 FCM(173)=-7.03741E-01 FCM(174)=-6.75251E-01 FCM(175)=-7.37080E-01
FCM(176)=-8.16209E-01 FCM(177)=-6.69546E-01 FCM(178)=-5.48248E-01 FCM(179)=-6.99334E-01 FCM(180)=-8.33513E-01
FCM(181)=-9.41013E-01 FCM(182)=-1.01917E+00 FCM(183)=-1.06672E+00 FCM(184)=-1.06672E+00 FCM(185)= 3.88071E-01
FCM(186)=-7.05104E-01 FCM(187)=-7.03738E-01 FCM(188)=-6.75249E-01 FCM(189)=-7.37078E-01 FCM(190)=-8.16207E-01
FCM(191)=-6.69545E-01 FCM(192)=-5.48248E-01 FCM(193)=-6.99334E-01 FCM(194)=-8.33513E-01 FCM(195)=-9.41013E-01
FCM(196)=-1.01917E+00 FCM(197)=-1.06672E+00 FCM(198)=-1.06672E+00 FCM(199)= 3.88071E-01 FCM(200)=-7.05099E-01
FCM(201)=-7.03734E-01 FCM(202)=-6.75246E-01 FCM(203)=-7.37075E-01 FCM(204)=-8.16205E-01 FCM(205)=-6.69543E-01
FCM(206)=-5.48248E-01 FCM(207)=-6.99334E-01 FCM(208)=-8.33513E-01 FCM(209)=-9.41013E-01 FCM(210)=-1.01917E+00
FCM(211)=-1.06672E+00 FCM(212)=-1.06672E+00 FCM(213)= 3.88073E-01 FCM(214)=-7.05087E-01 FCM(215)=-7.03721E-01
FCM(216)=-6.75237E-01 FCM(217)=-7.37068E-01 FCM(218)=-8.16198E-01 FCM(219)=-6.69539E-01 FCM(220)=-5.48248E-01
FCM(221)=-6.99334E-01 FCM(222)=-8.33513E-01 FCM(223)=-9.41013E-01 FCM(224)=-1.01917E+00 FCM(225)=-1.06672E+00
FCM(226)=-1.06672E+00 FCM(227)= 3.88070E-01 FCM(228)=-7.05109E-01 FCM(229)=-7.03743E-01 FCM(230)=-6.75253E-01
FCM(231)=-7.37081E-01 FCM(232)=-8.16211E-01 FCM(233)=-6.69546E-01 FCM(234)=-5.48248E-01 FCM(235)=-6.99334E-01
FCM(236)=-8.33513E-01 FCM(237)=-9.41013E-01 FCM(238)=-1.01917E+00 FCM(239)=-1.06672E+00 FCM(240)=-1.06672E+00
FCM(241)= 1.00000E-30 FCM(242)= 1.00000E-30 FCM(243)= 1.00000E-30 FCM(244)= 1.00000E-30 FCM(245)= 1.00000E-30
FCM(246)= 1.00000E-30 FCM(247)= 1.00000E-30 FCM(248)= 1.00000E-30 FCM(249)= 1.00000E-30 FCM(250)= 1.00000E-30
FCM(251)= 1.00000E-30 FCM(252)= 1.00000E-30 FCM(253)= 1.00000E-30 FCM(254)= 1.00000E-30 FCM(255)= 1.00000E-30
FCM(256)= 1.00000E-30 FCM(257)= 1.00000E-30 FCM(258)= 1.00000E-30 FCM(259)= 1.00000E-30 FCM(260)= 1.00000E-30
FCM(261)= 1.00000E-30 FCM(262)= 1.00000E-30 FCM(263)= 1.00000E-30 FCM(264)= 1.00000E-30 FCM(265)= 1.00000E-30
FCM(266)= 1.00000E-30 FCM(267)= 1.00000E-30 FCM(268)= 1.00000E-30 FCM(269)= 1.00000E-30 FCM(270)= 1.00000E-30
FCM(271)= 1.00000E-30 FCM(272)= 1.00000E-30 FCM(273)= 1.00000E-30 FCM(274)= 1.00000E-30 FCM(275)= 1.00000E-30
FCM(276)= 1.00000E-30 FCM(277)= 1.00000E-30 FCM(278)= 1.00000E-30 FCM(279)= 1.00000E-30 FCM(280)= 1.00000E-30
FCM(281)= 1.00000E-30 FCM(282)= 1.00000E-30 FCM(283)= 4.99862E-04 FCM(284)= 5.00121E-04 FCM(285)= 5.00157E-04
FCM(286)= 5.00199E-04 FCM(287)= 5.00248E-04
1 AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
CHARACTERISTICS OF HIGH LIFT AND CONTROL DEVICES
WING PLAIN TRAILING-EDGE FLAP CONFIGURATION
PLAIN FLAPS ON WING, EXAMPLE PROBLEM 5, CASE 2
----------------------- 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 4.2600E+06 2.250 0.822 3.000 2.600 0.000
0 ---------INCREMENTS DUE TO DEFLECTION--------- ---DERIVATIVES (PER DEGREE)---
0 DELTA D(CL) D(CM) D(CL MAX) D(CD MIN) (CLA)D (CH)A (CH)D
0.0 0.000 0.0000 0.000 0.00000 NDM -3.847E-03 -9.630E-03
0.1 0.001 -0.0004 0.001 0.00001 NDM -9.630E-03
0.2 0.002 -0.0009 0.002 0.00003 NDM -9.630E-03
0.3 0.002 -0.0013 0.003 0.00004 NDM -9.630E-03
0.4 0.003 -0.0017 0.003 0.00005 NDM -9.630E-03
0.6 0.005 -0.0026 0.005 0.00008 NDM -9.630E-03
0 *** NOTE * HINGE MOMENT DERIVATIVES ARE BASED ON TWICE THE AREA-MOMENT OF THE CONTROL ABOUT ITS HINGE LINE
0 --------- INDUCED DRAG COEFFICIENT INCREMENT , D(CDI) , DUE TO DEFLECTION ---------
0 DELTA = 0.0 0.1 0.2 0.3 0.4 0.6
ALPHA
0
-2.0 -1.40E-06 -1.39E-05 -2.77E-05 -4.13E-05 -5.48E-05 -8.14E-05
0.0 6.85E-10 6.85E-08 2.74E-07 6.16E-07 1.10E-06 2.46E-06
2.0 1.40E-06 1.40E-05 2.82E-05 4.25E-05 5.70E-05 8.63E-05
4.0 2.79E-06 2.80E-05 5.62E-05 8.44E-05 1.13E-04 1.70E-04
8.0 5.59E-06 5.60E-05 1.12E-04 1.68E-04 2.25E-04 3.38E-04
12.0 8.41E-06 8.39E-05 1.68E-04 2.52E-04 3.36E-04 5.05E-04
16.0 1.12E-05 1.12E-04 2.24E-04 3.36E-04 4.48E-04 6.73E-04
20.0 1.40E-05 1.40E-04 2.80E-04 4.20E-04 5.60E-04 8.41E-04
24.0 1.68E-05 1.68E-04 3.36E-04 5.04E-04 6.72E-04 1.01E-03
0***NDM PRINTED WHEN NO DATCOM METHODS EXIST
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1 THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE.
0
1 END OF JOB.
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