Oscillating delta wings with attached shock waves-Reference-Cited by-同舟云学术

Oscillating delta wings with attached shock waves

Published:1977-06 Issue:6 Volume:15 Page:804-812
ISSN:0001-1452
Container-title:AIAA Journal
language:en
Short-container-title:AIAA Journal

Author:

Liu D. D.¹,Hui W. H.²

Affiliation:

1. Northrop Corporation, Hawthorne, Calif.

2. University of Waterloo, Ontario, Canada

Publisher

American Institute of Aeronautics and Astronautics (AIAA)

Subject

Aerospace Engineering

Link

http://arc.aiaa.org/doi/pdf/10.2514/3.7371

Reference26 articles.

1. Dynamic stability testing of aircraft—needs versus capabilities

2. Exact and Approximate Solutions for the Supersonic Delta Wing

3. NUMERICAL SOLUTION OF THE PROBLEM OF SUPERSONIC FLOW PAST THE LOWER SURFACE OF A DELTA WING

4. 5Voskresenskii, G.P. "Numerical Solution of the Problem of a Supersonic Gas Flow Past an Arbitrary Surface of a Delta Wing in the Compression Region," Izv. Akad. Nauk SSR, Mekh. Zhidk., Gaza, No. 4,1968,134-142.

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