Pressure Gradient Effects on Supersonic Transition over Axisymmetric Bodies at Incidence-Reference-Cited by-同舟云学术

Pressure Gradient Effects on Supersonic Transition over Axisymmetric Bodies at Incidence

Published:2015-12 Issue:12 Volume:53 Page:3737-3751
ISSN:0001-1452
Container-title:AIAA Journal
language:en
Short-container-title:AIAA Journal

Author:

Tokugawa Naoko¹,Choudhari Meelan²,Ishikawa Hiroaki³,Ueda Yoshine⁴,Fujii Keisuke,Atobe Takashi,Li Fei,Chang Chau-Lyan,White Jeffery

Affiliation:

1. Japan Aerospace Exploration Agency, Tokyo 181-0015, Japan

2. Computational Aero Sciences Branch, NASA Langley Research Center, Hampton, Virginia 23681

3. ASIRI, Inc., Tokyo 163-1343, Japan

4. Tryangle, Inc., Tokyo 160-0023, Japan

Publisher

American Institute of Aeronautics and Astronautics (AIAA)

Subject

Aerospace Engineering

Link

http://arc.aiaa.org/doi/pdf/10.2514/1.J054070

Reference19 articles.

1. VijgenP. M. H. W.HolmesB. J. “Experimental and Numerical Analyses of Laminar Boundary-Layer Flow Stability over an Aircraft Fuselage Forebody,” Research in Natural Laminar Flow and Laminar-Flow Control, Part 3, NASA CP-2487, 1987, pp. 861–886.

2. Lecture Series 2005–06;Kroo I.,2005

3. DoughertyN. S.FisherD. F. “Boundary Layer Transition on a 10-Degree Cone: Wind Tunnel/Flight Data Correlation,” AIAA Paper 1980-0154, 1980.

4. Boundary-layer transition on a cone and flat plate at Mach 3.5

5. Three-dimensional boundary-layer transition on a cone at Mach 3.5

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