Calculation of the three-dimensional flow field in supersonic inlets at angle of attack using a bicharacteristic method with discrete shock wave fitting
Author:
Affiliation:
1. Purdue University, West Lafayette, Ind.
2. NASA, Lewis Research Center, Wind Tunnel and Flight Div., Cleveland, Ohio
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.1979-379
Reference11 articles.
1. The numerical solution of hyperbolic systems of partial differential equations in three independent variables
2. �ber die partiellen Differenzengleichungen der mathematischen Physik
3. Ransom, V.H., Hoffman, J.D., and Thompson, H.D. "A Second-Order Numerical Method o f Characteristics for Three-Dimensional Supersonic Flow, Val. I, Theoretical Development and Results,'' Report No. AFAPL-TR-69-98, A i r Force Aero Propulsion Laboratory, Wright-Patterson A i r Force Base, Ohio, October 1969.
Cited by 3 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. Calculation of High-speed Inlet Flows Using the Navier-Stokes Equations;Journal of Aircraft;1981-09
2. Improved Calculation of High Speed Inlet Flows: Part I. Numerical Algorithm;AIAA Journal;1981-01
3. Improved numerical simulation of high speed inlets using the Navier-Stokes equations;18th Aerospace Sciences Meeting;1980-01-14
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