Unsteady transonic algorithm improvements for realistic aircraft applications
Author:
Affiliation:
1. NASA, Langley Research Center, Hampton, VA
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.1988-105
Reference15 articles.
1. ANALYSIS OF EMBEDDED SHOCK WAVES CALCULATED BY RELAXATION METHODS
Cited by 6 articles. 订阅此论文施引文献 订阅此论文施引文献,注册后可以免费订阅5篇论文的施引文献,订阅后可以查看论文全部施引文献
1. Observations on three-dimensional nonlinear transonic wall-interference assessment and correction using semispan wing data;Computers & Fluids;1999-05
2. Computation of vortex-dominated flow for a delta wing undergoing pitching oscillation;AIAA Journal;1990-09
3. Wing-flutter calculations with the CAP-TSD unsteady transonic small-disturbance program;Journal of Aircraft;1989-09
4. Unsteady transonic algorithm improvements for realistic aircraft applications;Journal of Aircraft;1989-02
5. Modern wing flutter analysis by computational fluid dynamics methods;Journal of Aircraft;1988-10
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