Computation of unsteady transonic flows by the indicial method
Author:
Affiliation:
1. NASA, Ames Research Center, U.S. Army Air Mobility Research and Development Laboratory, Moffett Field, Calif.
2. Informatics Corp., Palo Alto, Calif.
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.1977-447
Reference13 articles.
1. 2hlers,F. E. "A Finite Difference Method for the Solution of the Transonic Flow Around Harmonically OcillatingWings ,"CR-2257, 1974, NASA.
2. 3eatherill,W. H., Sabastian, J. D., and Ehlere, I? E. "On the Computation of the Traneonic Perturbation Flow Fields Around Two- and Three-Drmeneional Oscillating Winga,"AIAA Paper 76-99,'m. 1976.
3. Sraci,R. M., Albano, E, D., and Farr, J. L. "Small-Disturbance Transonic Flowa About Cscillating Airfoils and Planar Wings ,'' hFFDL-TR-75-10, June 1975.
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1. Calculation of three-dimensional unit impulse response using nonlinear transonic flow equations;23rd Atmospheric Flight Mechanics Conference;1998-08-10
2. Time-Dependent Response of a Two-Dimensional Airfoil in Transonic Flow;AIAA Journal;1979-01
3. Implicit Finite-Difference Computations of Unsteady Transonic Flows about Airfoils;AIAA Journal;1977-12
4. An implicit shock-fitting scheme for unsteady transonic flow computations;3rd Computational Fluid Dynamics Conference;1977-06-27
5. Unsteady transonic flows around oscillating wings;Tenth International Conference on Numerical Methods in Fluid Dynamics
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