Numerical simulation of supersonic inlets using a three-dimensional viscous flow analysis
Author:
Affiliation:
1. NASA, Lewis Research Center, Cleveland, Ohio
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.1980-384
Reference21 articles.
1. Paynter, G.C. "Analysis of Weak Glancing Shock/Boundary Layer Interactions," AIM Paper 79-01114, January 1.979.
2. Mach 3 oblique shock wave/turbulent boundary layer interactions in three dimensions
3. Numerical Solution of Three-Dimensional Shock Wave and Turbulent Boundary-Layer Interaction
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1. Quantitative laser velocimetry measurements in the hypersonic regimeby the integration of experimental and computational analysis;31st Aerospace Sciences Meeting;1993-01-11
2. Numerical investigation of supersonic mixed-compression inlet using an implicit upwind scheme;Journal of Propulsion and Power;1992-01
3. Numerical simulation of a supersonic inlet;29th Aerospace Sciences Meeting;1991-01-07
4. Evolution and application of CFD techniques for scramjet engine analysis;Journal of Propulsion and Power;1987-09
5. A study of a supersonic axisymmetric spiked inlet at angle of attackusing the Navier-Stokes equations;24th Aerospace Sciences Meeting;1986-01-06
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