Visualization of Supersonic Boundary-Layer Transition on a 10-Degree Cone Model Using Temperature-Sensitive Paint(Fluids Engineering)-Reference-Cited by-同舟云学术

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Visualization of Supersonic Boundary-Layer Transition on a 10-Degree Cone Model Using Temperature-Sensitive Paint(Fluids Engineering)

Published:2010 Issue:762 Volume:76 Page:259-265
ISSN:0387-5016
Container-title:Transactions of the Japan Society of Mechanical Engineers Series B
language:en
Short-container-title:Trans.JSME, Ser.B

Author:

EGAMI Yasuhiro¹,IIJIMA Yoshimi,ASAI Keisuke

Affiliation:

1. Department of Micro-Nano Systems Engineering, Nagoya University

Publisher

Japan Society of Mechanical Engineers

Subject

Mechanical Engineering,Condensed Matter Physics

Link

https://www.jstage.jst.go.jp/article/kikaib1979/76/762/76_KJ00006164615/_pdf

Reference13 articles.

1. 1) DOUGHERTY N. S. Jr. Boundary-layer transition on a 10-deg cone : wind tunnel/ flight correlation. (1980)

2. 2) SAWADA H. The NAL 0.2m Supersonic Wind Tunnel. (1996)

3. 3) ASAI K. Visualization of the Quiet Wind Tunnel using Luminescent Paint. International Congress on Instrumentation in Aerospace Simulation Facilities, ICIASF'97 Record. (1997) p.84-85.

4. 4) OKUWA T. Prediction and validation of supersonic boundary layer transition on 10deg cone. Proceedings of the 29th and 30th NAL Workshops on Investigation and Control of Boundary-Layer Transition, 2002. (2002) p.53-56.

5. 5) CAMPBELL B. T. Temperature sensitive fluorescent paint systems. (1994)

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