79. Farhat, C., Geuzaine, P., Brown, G., and Harris, C., “Nonlinear Flutter Analysis <strong>of</strong> an F- 16 in Stabilized, Accelerated, and Increased Angle <strong>of</strong> Attack Flight Conditions,” AIAA Paper 2002-1490, April 2002. 80. Tang, L., Bartels, R. E., Chen, P. C., and Liu, D. D., “Simulation <strong>of</strong> transonic limit cycle oscillations using a CFD time-marching method,” AIAA Paper 2001-1290, April 2001. 81. Bendiksen, O. O., “Transonic Limit Cycle Flutter/LCO,” AIAA Paper 2004-1694, April 2004. 82. Dubben, J. A., and Denegri, C. M., Jr., “Underwing Missile Aerodynamic Effects on Flight-Measured Limit Cycle Oscillations,” AIAA Paper 2007-1801, April 2007. 83. Rizk, M., Ellison, S., and Prewitt, N. C., “Beggar – A St<strong>or</strong>e Separation Predictive Tool”; AIAA Paper 02-3190, June 2002. 84. Rizk, M., Westm<strong>or</strong>eland, W.S., and Lee, J.M., “Beggar Code Implementation <strong>of</strong> 6+DOF Capability f<strong>or</strong> St<strong>or</strong>es with Moving Components.” AIAA Paper 2004-1251, January 2004. 85. Noack, R.W., and Jolly, B., “Fully Time Accurate CFD Simulations <strong>of</strong> JDAM Separation from an F-18C Aircraft.” AIAA Paper 2000-0794, January 2000. 86. Brock, J., and Jolly, B., “Application <strong>of</strong> Computational Fluid Dynamics at Eglin Air F<strong>or</strong>ce Base.” SAE 985500. 87. Freeman, J. A., and Jolly, B. A., “Applied Computational Fluid Dynamics in Supp<strong>or</strong>t <strong>of</strong> Aircraft/St<strong>or</strong>e Compatibility and Weapons Integration – 2004 Edition,” Proceedings <strong>of</strong> the Users Group Conference (DOD_UGC’04), pp. 0-7695-2259-9/04, 2004. 88. M<strong>or</strong>an, Robert. "Fluid and Structure Interaction Toolkit (FASIT)," Air F<strong>or</strong>ce SEEK EAGLE Office, Eglin AFB, FL, 21 Feb. 2008. 89. Maxwell, D. L., Denegri, C. M., Jr., Dawson, K. S., and Dubben, J. A., “Effect <strong>of</strong> Underwing St<strong>or</strong>e Aerodynamics on Analytically Predicted F-16 Aeroelastic Instability,” AIAA Paper 2007-2366, April 2007. 90. M<strong>or</strong>ton, S. A., McDaniel, D. R., and Cummings, R. M., “F-16XL Unsteady Simulations f<strong>or</strong> the CAWAPI Facet <strong>of</strong> RTO Task Group AVT-113,” AIAA Paper 2007-493, January 2007. 91. Parker, G. H., Maple, R. C., and Beran, P. S., “Computational Aeroelastic Analysis <strong>of</strong> St<strong>or</strong>e-Induced Limit-Cycle Oscillation,” Journal <strong>of</strong> Aircraft, Vol. 44, No. 1, Jan-Feb 2007, pp. 48-59. 92. Parker, G. H., Maple, R. C., and Beran, P. S., “Analysis <strong>of</strong> St<strong>or</strong>e Effects on Limit-Cycle Oscillation,” AIAA Paper 2006-1816, May 2006. 168
93. Parker, G. H., Maple, R. C., and Beran, P. S., “The Role <strong>of</strong> Viscosity in St<strong>or</strong>e-Induced Limit-Cycle Oscillation,” AIAA Paper 2005-1916, April 2005. 94. M<strong>or</strong>ton, S. A., McDaniel, D. R., Sears, D. R., Tillman, B., and Tuckey, T. R., “Kestrel: A Fixed Wing Virtual Aircraft Product <strong>of</strong> the CREATE Program,” AIAA Paper 2009-338, January 2009. 95. United States, Computational Sciences Center <strong>of</strong> Excellence, Air F<strong>or</strong>ce Research Lab<strong>or</strong>at<strong>or</strong>y, “Air Vehicles Unstructured Solver (AVUS) User's Manual,” Wright- Patterson AFB, 2000. 96. McDaniel, D. R. and M<strong>or</strong>ton, S. A., “Efficient Mesh Def<strong>or</strong>mation f<strong>or</strong> Computational Stability and Control Analyses on Unstructured Viscous Meshes,” AIAA Paper 2009- 1363, January 2009. 97. Godunov, S. K., “A Finite Difference Method f<strong>or</strong> the Computation <strong>of</strong> Discontinuous Solutions <strong>of</strong> the Equations <strong>of</strong> Fluid Dynamics”, Mat. Sb., 47:357-393, 1959. 98. Spalart, P.R., Allmaras, S.R., “A One-equation Turbulence Model f<strong>or</strong> Aerodynamic Flows,” AIAA Paper 92-0439, January 1992. 99. Shur, M.L., Strelets, M.K., Travin, A.K., Spalart, P.R., “Turbulence Modeling in Rotating and Curved Channels: Assessing the Spalart-Shur C<strong>or</strong>rection,” AIAA Journal, Vol. 38, No. 5, May 2000. 100. Spalart, P.R., Jou, W-H., Strelets, M., Allmaras, S.R., “Comments on the Feasibility <strong>of</strong> LES f<strong>or</strong> Wings, and on a Hybrid RANS/LES Approach,” Proceedings <strong>of</strong> the First AFOSR International Conference on DNS/LES, Greyden Press, Aug 1997. 101. Menter, F.R., “Zonal Two Equation k-ω Turbulence Models f<strong>or</strong> Aerodynamic Flows,” AIAA Paper 1993-2906, July 1993. 102. Strelets, M. “Detached Eddy Simulation <strong>of</strong> Massively Separated Flows”, AIAA Paper 2001-0879, January 2001. 103. Wilcox, D.C., Turbulence Modeling f<strong>or</strong> CFD, Second Edition, DCW Industries, Inc., 1998. 104. Strang, W. Z., Tomaro, R. F., and Grismer, M. J., “The Defining Methods <strong>of</strong> Cobalt60: A Parallel, Implicit, Unstructured Euler/Navier-Stokes Flow Solver,” AIAA Paper 1999- 0786, January 1999. 105. Tomaro, R. F., Strang, W. Z., and Sankar, L. N., “An Implicit Alg<strong>or</strong>ithm f<strong>or</strong> Solving Time Dependent Flows on Unstructured Grids,” AIAA Paper 1997-0333, January 1997. 106. Grismer, M. J., Strang, W. Z., Tomaro, R. F., and Witzemman, F. C., “Cobalt: A Parallel, Implicit, Unstructured Euler/Navier-Stokes Solver,” Adv. Eng. S<strong>of</strong>tware, Vol. 29, No. 3- 6, pp. 365-373, 1998. 169
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TEMPORAL ANALYSIS OF TRANSONIC FLOW
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To Dodjie 3
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TABLE OF CONTENTS ACKNOWLEDGMENTS .
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Summary ...........................
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LIST OF FIGURES Figure page 2-1 F-1
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6-9 Lissajous plots of upper surfac
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6-45 2-D (left column) and 3-D (rig
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incrementally since this capability
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are not sufficient to provide an an
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4. Contribute to the work of others
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Classical aircraft flutter is chara
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Popular methods for finding the sol
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LCO amplitude but not the mechanism
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speed for the particular configurat
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Denegri 23 explains the flutter fli
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Doublet-lattice Denegri 1, 7,12,13
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Batina’s work and uses an F-16 ha
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As a result of Denegri’s previous
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Figure 2-1. F-16 store stations. Fi
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Figure 2-5. Flutter flight test bui
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Stokes (RANS) equations on hybrid u
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CHAPTER 4 ANALYSIS TECHNIQUES Intro
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time-localization cannot be determi
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A B C D E Figure 4-3. Analysis of s
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(CFD) analyses in order to capture
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the appropriate time step for the n
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Wing1, is the wing-only (no fuselag
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similar to DES but with modificatio
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Figure 5-1. Time step comparison of
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A B Figure 5-3. Flow results for 8
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A B Figure 5-5. Flow results for 8
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Figure 5-7. Turbulence model compar
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Figure 5-9. CFD vs. wind tunnel com
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Figure 5-11. CFD vs. wind tunnel co
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Figure 5-13. CFD vs. wind tunnel co
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server cluster comprised of 5,120 p
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of oscillation. The 88% span locati
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since it is proportional to lift, a
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of phase. Figure 6-10 B) and D) are
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The instantaneous Cp measurements p
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D Lissajous plots with time being t
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frequency of 8Hz. The wavelet plot
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vortex is observed travelling outbo
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near 70% chord and the second near
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expected from a lift curve slope. A
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shape of this Lissajous is nonlinea
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occurring at harmonics, and assumes
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the same direction of rotation on t
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the roll cycle, and the black arrow
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B) shows the fast Fourier transform
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is that shock separation aft of the
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on the upper surface, a much larger
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Figure 6-1. F-16 wing planform with
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A C B Figure 6-4. DDES of F-16 in s
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Cp (Non-dimensional) Cp (Non-dimens
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-Cp (Non-dimensional) A -Cp (Non-di
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-Cp (Non-dimensional) A -Cp (Non-di
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-Cp (Non-dimensional) A Time (sec)
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