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53. Batina, J. T., "Efficient Algorithm for Solution of the Unsteady Transonic Small- Disturbance Equation," Journal of Aircraft, Vol. 25, July 1988, pp. 598-605. 54. Batina, J. T., "Unsteady Transonic Flow Calculations for Interfering Lifting Surface Configurations," Journal of Aircraft, Vol. 23, May 1986, pp. 422-430. 55. Batina, J. T., "Unsteady Transonic Flow Calculations for Wing-Fuselage Configurations," Journal of Aircraft, Vol. 23, Dec. 1986, pp. 897-903. 56. Bennett, R. M., Bland, S. R., Batina, J. T., Gibbons, M. D., and Mabey, D. G., "Calculation of Steady and Unsteady Pressures on Wings at Supersonic Speeds with a Transonic Small-Disturbance Code," AIAA Paper 87-0851, April 1987. 57. Batina, J. T., Seidel, D. A., Bland, S. R., and Bennett, R. M., "Unsteady Transonic Flow Calculations for Realistic Aircraft Configurations," AIAA Paper 87-0850, April 1987. 58. Bennett, R. M., Batina, J. T., and Cunningham, H. J., “Wing-Flutter Calculations with the CAP-TSD Unsteady Transonic Small-Disturbance Program,” Journal of Aircraft, Vol. 26, No. 9, 1989, pp. 876-882. 59. Bennett, R. M., Batina, J. T., and Cunningham, H. J., “Wing-Flutter Calculations with the CAP-TSD Unsteady Transonic Small-Disturbance Program,” AIAA Paper 1988-2347, April 1988. 60. Cunningham, H. J., Batina, J. T., and Bennett, R. M., “Modern wing flutter analysis by computational fluid dynamics methods,” Journal of Aircraft, Vol. 25, No. 10, 1988. pp. 962-968. 61. Haller, R. L., “CAP-TSD Evaluation,” Proceedings of the Aerospace Flutter and Dynamics Council Meeting, May 1989. 62. Feldman, C. S., “Wind Tunnel Data Report, 1/9-Scale F-16C Pressure Loads Test,” General Dynamics, Report 16PR2252, July 1982. 63. Pitt, D. M., Fuglsang, D. F., and Drouin, D. V., “Application of XTRAN3S and CAP- TSD to Fighter Aircraft,” Journal of Aircraft, Vol. 28, No. 10, 1991, pp. 657-663. 64. Denegri, C. M., Jr., and Dubben, J. A., “F-16 Limit Cycle Oscillation Analysis Using Transonic Small-Disturbance Theory,” AIAA Paper 2005-2296, April 2005. 65. Denegri, C. M., Jr., and Dubben, J. A., “F-16 Limit Cycle Oscillation Stability Boundary from Transonic Small-Disturbance Theory,” IFASD paper IF-010, Proceedings of the International Forum on Aeroelasticity and Structural Dynamics, Munich, Germany, June 2005. 66. Air Vehicles Directorate AFRL/VA, "AFRL-Developed Simulation Tool Improves Aircraft-Stores Carriage Certification Process," Air Force Print News Today, 29 August 2007, January 2008 . 166
67. Cunningham, A. M., Jr., and den Boer, R. G., “Transonic Wind Tunnel Investigation of Limit Cycle Oscillations on Fighter Type Wings - Update,” AIAA Paper 1992-2125, April 1992. 68. Cunningham, A. M., Jr., “General Wind Tunnel Test Report for Limit Cycle Oscillation Test,” General Dynamics, Report 16PR10965, June 1992. 69. Cunningham, A. M., Jr., “Final Report for F-16 Limit Cycle Oscillation Investigation: Volume III – A Semi-Empirical Method for Predicting Transonic Limit Cycle Oscillation Characteristics of Fighter Aircraft, Part 2 – Pressure Time History Analysis and Development of the LFWC Unsteady Aerodynamic Model for LCO,” Lockheed Fort Worth Company, Report 16PR11861, June 1994. 70. Cunningham, A. M., Jr., and den Boer, R. G., “Overview of Unsteady Transonic Wind Tunnel Test on a Semispan Straked Delta Wing Oscillating in Pitch,” Wright Laboratory, Report WL-TR-94-3017, August 1994. 71. Cunningham, A. M., Jr., “A Generic Nonlinear Aeroelastic Method with Semi-empirical Nonlinear Unsteady Aerodynamics - Volume 1: Technical Discussion,” Air Force Research Laboratory, Report AFRL-VA-WP-TR-1999-3014, February 1999. 72. Cunningham, A. M., Jr., “The Role of Non-linear Aerodynamics in Fluid-Structure Interaction,” AIAA Paper 1998-2423, June 1998. 73. Meijer, J. J., and Cunningham, A. M., Jr., “Understanding and Development of a Prediction Method of Transonic Limit Cycle Oscillation Characteristics of Fighter Aircraft,” AIAA Paper 1992-4501, 1992. 74. Cunningham, A. M., Jr., and Meijer, J. J., “Semi-Empirical Unsteady Aerodynamics for Modeling Aircraft Limit Cycle Oscillations and Other Non-Linear Aeroelastic Problems,” Proceedings of the International Forum on Aeroelasticity and Structural Dynamics, Royal Aeronautical Society, London, Vol. 2, 1995, pp. 74.1-74.14. 75. Meijer, J. J., and Cunningham, A. M., Jr., “A Semi-Empirical Unsteady Nonlinear Aerodynamic Model to Predict Transonic LCO Characteristics of Fighter Aircraft,” AIAA Paper 1995-1340, April 1995. 76. Cunningham, A. M., Jr., “Aerodynamic Aspects of Transonic Limit Cycle Oscillations,” 1994 Proceedings of the Aeroelasticity and Fluid Structure Interaction Problems, American Society of Mechanical Engineers, Chicago, Vol. 44, 1994, pp. 29-47. 77. Melville, R., “Nonlinear Simulation of F-16 Aeroelastic Instability,” AIAA Paper 2001- 0570, January 2001. 78. Melville, R., “Nonlinear Mechanisms of Aeroelastic Instability for the F-16,” AIAA Paper 2002-0817, January 2002. 167
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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
Page 115 and 116: -Cp (Non-dimensional) A Time (sec)
Page 117 and 118: A B Figure 6-14. DDES-SARC of F-16
Page 119 and 120: Cp (Non-dimensional) Cp (Non-dimens
Page 121 and 122: Figure 6-18. Lissajous plots of upp
Page 123 and 124: -Cp (Non-dimensional) Frequency (Hz
Page 125 and 126: -Cp (Non-dimensional) A Frequency (
Page 133 and 134: -Cp (Non-dimensional) A -Cp (Non-di
Page 135 and 136: -Cp (Non-dimensional) A -Cp (Non-di
Page 143 and 144: A B D Figure 6-40. DDES of F-16 in
Page 157 and 158: Impact on Future Design of Aircraft
Page 159 and 160: The size of the Mach=1 iso-surface
Page 161 and 162: these cases in order to identify th
Page 163 and 164: 15. Dawson, K. S., and Sussinham, J
Page 165: 41. Thomas, J. P., Dowell, E. H., a
Page 169 and 170: 93. Parker, G. H., Maple, R. C., an
Page 171 and 172: 121. Travin, A. K., Shur, M. L., Sp
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