Aircraft Stability Analysis Including Unsteady Aerodynamic Effects

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41Figure 1-15 C l vs. roll angle histogram for one cycle of wing rock at θ 0 = 27 degree .Data extracted from [45].
42Figure 1-16 C l vs. roll angle histogram for one cycle of wing rock at θ 0 = 32 degree.Data extracted from [45].21.51C N0.50φ = 0φ = 10φ = 20φ = 30-0.5-10 0 10 20 30 40 50α [deg]Figure 1-17 Normal force coefficient in balance coordinates vs. pitch angle – resultsfrom static tests. Data extracted from [47].
Page 1 and 2:
An Investigation of Unsteady Aerody
Page 3 and 4: iAcknowledgmentsAll that I struggle
Page 10 and 11: Figure 3-19 Roll angle time history
Page 12 and 13: 0( α )x static dependence function
Page 14 and 15: 11 IntroductionThe atmospheric flig
Page 16 and 17: 3aerodynamic forces in terms of the
Page 18 and 19: 5another state-space representation
Page 20 and 21: 7a nonlinear indicial response theo
Page 22 and 23: 9Figure 1-2 Internal state-space va
Page 24 and 25: 11representation, we write it expli
Page 26 and 27: 13C& α cV() t = C ( α ) + C C ()
Page 28 and 29: 15(a)(b)*Figure 1-3 Influence of th
Page 30 and 31: 17( α )1x0 U eff=1+exp(1-13)[ −
Page 32 and 33: 19tˆ =c2V, (1-17)c being a charact
Page 34 and 35: 21representing forward and aft fuse
Page 36 and 37: 23In equation (1-19)∗αwdescribes
Page 38 and 39: 25Ntiα2( x ) = a + b x c xC +tit1
Page 40 and 41: 27The rolling moment of the aircraf
Page 42 and 43: 29are the A-4 Skyhawk, F-4 Phantom,
Page 44 and 45: 31Conventional wing rock is that oc
Page 46 and 47: 33Figure 1-8 Crossflow streamlines
Page 48 and 49: 35possible cases forC φ, where the
Page 50 and 51: 37Figure 1-10 Roll angle time-histo
Page 52 and 53: 39Figure 1-14 Rolling moment coeffi
Page 56 and 57: 430.020-0.02C l-0.04-0.06-0.08φ =
Page 58 and 59: 451.2.3 Analytical and Computationa
Page 60 and 61: 47vertical fin inclusion, the oscil
Page 62 and 63: 49Table 1-1 Geometrical and physica
Page 64 and 65: 51Figure 1-22 Free to roll apparatu
Page 66 and 67: 53Both of these problems make it di
Page 68 and 69: 55experimental results the values o
Page 70 and 71: 57► State equations:τdxi1,x+ xi=
Page 72 and 73: 592.2 The Second Unsteady Aerodynam
Page 74 and 75: 61With the help of the formulation
Page 76 and 77: 63tunnel tests results shown in Fig
Page 78 and 79: 65C2( ν ) = a + b ν c νN i 6 6 i
Page 80 and 81: 67Figure 2-2 Static model responses
Page 82 and 83: 69Figure 2-4 Variation of the norma
Page 84 and 85: 71When the quasi-static sequences o
Page 86 and 87: 73identification. The static data u
Page 88 and 89: 752( x ) - 7.293 x - 5.427 xCN i= 0
Page 90 and 91: 77Figure 3-1 Static normal force co
Page 92 and 93: Figure 3-3 Identified static values
Page 94 and 95: Figure 3-5 Rolling moment coefficie
Page 100 and 101: 87with the roll angle, and attains
Page 102 and 103: 890.060.04θ = 20 degModel response
Page 104 and 105:
9140θ = 27 deg20φ, deg0-20-4015.6
Page 106 and 107:
93C l0.150.1θ = 27 degModel respon
Page 108 and 109:
95C l0.150.1θ = 38 degModel respon
Page 110 and 111:
97100θ = 45 deg50φ, deg0-50-1000
Page 112 and 113:
990.060.04θ = 45 degModel response
Page 114 and 115:
101Table 3-1 Model parameters for t
Page 116 and 117:
103Table 3-3 Continuation of Table
Page 118 and 119:
Page 120 and 121:
Page 122 and 123:
109q, r, the Euler angles time rate
Page 124 and 125:
1114.3 Results of the SimulationsTh
Page 126 and 127:
Figure 4-2 Phase-plane of the simul
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Page 130 and 131:
Page 132 and 133:
Page 134 and 135:
121Considering these characteristic
Page 136 and 137:
123[10] Jones, R. T., “The Unstea
Page 138 and 139:
125[28] Goman, M. G., Stolyarov, G.
Page 140 and 141:
127[45] Nguyen, L. T., Yip L., Cham
Page 142 and 143:
129AppendicesAppendix AA.1 The Conv
Page 144 and 145:
131u = V cosθ 0v = Vsinθ0sinφw =
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Aircraft Stability Analysis Including Unsteady Aerodynamic Effects

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