Aircraft Stability Analysis Including Unsteady Aerodynamic Effects

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93C l0.150.1θ = 27 degModel responseExperimental data0.050-0.05-0.1-40 -30 -20 -10 0 10 20 30 40φ, degFigure 3-15 Rolling moment coefficient vs. roll angle loops at θ 0 = 27 deg.
9440θ = 38 deg20φ, deg0-20-4015.6 15.8 16 16.2 16.4 16.6 16.84038Left wingRight wingα, deg36343215.6 15.8 16 16.2 16.4 16.6 16.8time, sFigure 3-16 Roll angle time history for θ 0 = 38 deg (above), and corresponding angleof attack time history for each half-wing (below).
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An Investigation of Unsteady Aerody
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iAcknowledgmentsAll that I struggle
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Figure 3-19 Roll angle time history
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0( α )x static dependence function
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11 IntroductionThe atmospheric flig
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3aerodynamic forces in terms of the
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5another state-space representation
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7a nonlinear indicial response theo
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9Figure 1-2 Internal state-space va
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11representation, we write it expli
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13C& α cV() t = C ( α ) + C C ()
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15(a)(b)*Figure 1-3 Influence of th
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17( α )1x0 U eff=1+exp(1-13)[ −
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19tˆ =c2V, (1-17)c being a charact
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21representing forward and aft fuse
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23In equation (1-19)∗αwdescribes
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25Ntiα2( x ) = a + b x c xC +tit1
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27The rolling moment of the aircraf
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29are the A-4 Skyhawk, F-4 Phantom,
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31Conventional wing rock is that oc
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33Figure 1-8 Crossflow streamlines
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35possible cases forC φ, where the
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37Figure 1-10 Roll angle time-histo
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39Figure 1-14 Rolling moment coeffi
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41Figure 1-15 C l vs. roll angle hi
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 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 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
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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