A systematic development of the supersonic flow fields over and behind wings and wing-body configurations using a shock-capturing finite-difference approach-Reference-Cited by-同舟云学术

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A systematic development of the supersonic flow fields over and behind wings and wing-body configurations using a shock-capturing finite-difference approach

Published:1971-01-25 Issue: Volume: Page:
ISSN:
Container-title:9th Aerospace Sciences Meeting
language:
Short-container-title:

Author:

KUTLER P.¹,LOMAX H.¹

Affiliation:

1. NASA, AMES RESEARCH CENTER, MOFFETT FIELD, CALIF.

Publisher

American Institute of Aeronautics and Astronautics

Link

http://arc.aiaa.org/doi/pdf/10.2514/6.1971-99

Reference29 articles.

1. I. Kutler, P. "Application of Selected Finite Difference Techniques to the Solution of Conical Flow Problems," Ph.D. Thesis,Iowa State University, 1969.

2. Moretti, G. "The Choice of a Time-Dependent Technique in GasDynamics," PIBAL Report 69-26, 1969.

Cited by 8 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. Efficient and accurate numerical solutions of the Euler and Navier-Stokes equations for turbomachinery applications;20th Joint Propulsion Conference;1984-06-11

2. Investigation of Crossflow Shocks on Delta Wings in Supersonic Flow;AIAA Journal;1980-01

3. Investigation of cross flow shocks on delta wings in supersonic flow;17th Aerospace Sciences Meeting;1979-01-15

4. Supersonic Flow about Ducted Bodies with Subsonic Internal Boundaries;Journal of Aircraft;1975-06

5. Studies of scramjet/airframe integration techniques for hypersonic aircraft;13th Aerospace Sciences Meeting;1975-01-20

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