Preliminary Study on Side-Wall Boundary Layers in Transonic Shock Tube Airfoil Testing-Reference-Cited by-同舟云学术

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Preliminary Study on Side-Wall Boundary Layers in Transonic Shock Tube Airfoil Testing

Published:2008-01-07 Issue: Volume: Page:
ISSN:
Container-title:46th AIAA Aerospace Sciences Meeting and Exhibit
language:
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Author:

Kashitani Masashi¹,Yamaguchi Yutaka¹,Sunahara Eisaku¹,Kitano Hideki¹

Affiliation:

1. National Defense Academy

Publisher

American Institute of Aeronautics and Astronautics

Link

http://arc.aiaa.org/doi/pdf/10.2514/6.2008-850

Reference13 articles.

1. 1R.A.Kilgore,AnIntroductiontoWindTunnelsandTestingTechnique,LectureSeriesatNDA,(1987).

2. 3W. J. Cook and D. E. Woicke, Shock Tube Study of NACA 0012 Airfoil Flows for Air and SF6 in A Test Section with Straight Walls, ISU ERI ReportNo.95402, July15,(1994).

3. Airfoil Flow Visualization and Pressure Measurements in High-Reynolds-Number Transonic Flow

Cited by 2 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. Effects of aspect ratio in a transonic shock tube airfoil flow;Journal of Thermal Science;2012-09-07

2. Preliminary Study on Diaphragmless Shock Tube for Transonic Airfoil Testing with PDI;48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition;2010-01-04

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