Aircraft Stability Analysis Including Unsteady Aerodynamic Effects

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127[45] Nguyen, L. T., Yip L., Chambers J. R., “Self-Induced Wing Rock of SlenderDelta Wings”, AIAA Paper 81-1883, AIAA AFM Conference, Albuquerque,New Mexico, August 1981.[46] Arena Jr. A., “An Experimental and Computational Investigation of SlenderWings undergoing Wing Rock”, Ph.D. dissertation, University of NotreDame, April 1992.[47] Levin, D., Katz, J., “Dynamic Load Measurements with Delta WingsUndergoing Self-Induced Roll Oscillations”, Journal of Aircraft, Vol. 21, No.1, pp. 30-36, 1984.[48] Ericson, L. E., “The Various Sources or Wing Rock”, AIAA Paper 88-4370,August, 1988.[49] Nguyen, L. T., Whipple, R. D. , and Brandon, J. M., “Recent Experiences ofUnsteady Aerodynamic Effects on Aircraft Flight Dynamics at High-Anglesof-Attack”,Paper 28, AGARD CP 386, 1985.[50] Ericson, L. E., “Wing Rock Generated by Forebody Vortices”, AIAA Paper87-0268, 1987.[51] Arena Jr., A., “An Experimental Study of the Nonlinear Wing RockPhenomenon”, Master´s Thesis, University of Notre Dame, April 1990.[52] Nelson, R. C., Pelletier, A., “The unsteady aerodynamics of slender wingsand aircraft undergoing large amplitude maneuvers”, Progress in AerospaceSciences 39 (2003) 185-248, Elsevier, 2003.[53] Konstadinopoulos, P., Mook, D. T., Nayfeh, A. H., “Subsonic Wing Rock ofSlender Delta Wings”, Journal of Aircraft, 22(3), pp. 223-228, March 1985.
128[54] Nayfeh, A. H., Elzebda, J. M., Mook, D. T., “Analytical Study of theSubsonic Wing-Rock Phenomenon for Slender Delta Wings”, Journal ofAircraft, Vol. 6, No. 9, September, 1989.[55] Saad, A. A., “Simulation and Analysis of Wing Rock Physics for a GenericFighter Model with Three Degrees-of-Freedom”, Ph.D. Dissertation, AirForce Institute of Technology, Dayton, Ohio, 2000.[56] Lagarias, J.C., J. A. Reeds, M. H. Wright, and P. E. Wright, “ConvergenceProperties of the Nelder-Mead Simplex Method in Low Dimensions”, SIAMJournal of Optimization, Vol. 9 Number 1, pp. 112-147, 1998.[57] Etkin, B., Dynamics of Atmospheric Flight, John Wiley and Sons, Inc. NewYork, 1972[58] Gainer, T.G., and Hoffman, S., “Summary of transformation equations andequations of motion used in free flight and wind tunnel data reduction andanalysis”, NASA-SP-3070, January 1972[59] Nelson, R. C., Flight Stability and Automatic Control, 2 nd Edition, Mc Graw-Hill, 1998[60] Durham, W., “AOE 5214 Course Notes and Problems Solutions”, VirginiaPolytechnic Institute and State University, Blacksburg, VA, 1997.
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
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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
Page 36 and 37:
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
Page 46 and 47:
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
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430.020-0.02C l-0.04-0.06-0.08φ =
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451.2.3 Analytical and Computationa
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47vertical fin inclusion, the oscil
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49Table 1-1 Geometrical and physica
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51Figure 1-22 Free to roll apparatu
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53Both of these problems make it di
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55experimental results the values o
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57► State equations:τdxi1,x+ xi=
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592.2 The Second Unsteady Aerodynam
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61With the help of the formulation
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63tunnel tests results shown in Fig
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65C2( ν ) = a + b ν c νN i 6 6 i
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67Figure 2-2 Static model responses
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69Figure 2-4 Variation of the norma
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71When the quasi-static sequences o
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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 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 142 and 143: 129AppendicesAppendix AA.1 The Conv
Page 144 and 145: 131u = V cosθ 0v = Vsinθ0sinφw =
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