Near-Field Experiments on Tip Vortices at Mach 3.1-Reference-Cited by-同舟云学术

Near-Field Experiments on Tip Vortices at Mach 3.1

Published:1997-04 Issue:4 Volume:35 Page:750-753
ISSN:0001-1452
Container-title:AIAA Journal
language:en
Short-container-title:AIAA Journal

Author:

Wang Frank Y.¹,Sforza Pasquale M.¹

Affiliation:

1. Polytechnic University, Brooklyn, New York 11201

Publisher

American Institute of Aeronautics and Astronautics (AIAA)

Subject

Aerospace Engineering

Link

http://arc.aiaa.org/doi/pdf/10.2514/2.172

Reference10 articles.

1. The Measurement of Downwash and Sidewash Behind a Rectangular Wing at a Mach Number of 1.6

2. Experimental study of shock-vortex interaction in a Mach 3 stream

3. An exploratory wind tunnel study of supersonic tip vortices

4. 5Wang, F. Y. “A Wind Tunnel Study of Supersonic Vortical Wakes from Tip Vortex Generators,” Ph.D. Dissertation,Dept. of Aerospace Engineering, Polytechnic Univ., Brooklyn, NY,June 1994.

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