APPLICATION OF SHOCK TUNNEL TO HEAT TRANSFER EXPERIMENTS ON TURBINE BLADE

Li Jingmei; Zhao Runming; Wang Jinan

Volume 2 Issue 1

Jan. 1987

Turn off MathJax

Article Contents

Article Navigation > Journal of Aerospace Power > 1987 > 2(1): 18-22,89

Li Jingmei, Zhao Runming, Wang Jinan. APPLICATION OF SHOCK TUNNEL TO HEAT TRANSFER EXPERIMENTS ON TURBINE BLADE[J]. Journal of Aerospace Power, 1987, 2(1): 18-22,89.

Citation:

Li Jingmei, Zhao Runming, Wang Jinan. APPLICATION OF SHOCK TUNNEL TO HEAT TRANSFER EXPERIMENTS ON TURBINE BLADE[J]. Journal of Aerospace Power, 1987, 2(1): 18-22,89.

Li Jingmei, Zhao Runming, Wang Jinan. APPLICATION OF SHOCK TUNNEL TO HEAT TRANSFER EXPERIMENTS ON TURBINE BLADE[J]. Journal of Aerospace Power, 1987, 2(1): 18-22,89.

Citation:

Li Jingmei, Zhao Runming, Wang Jinan. APPLICATION OF SHOCK TUNNEL TO HEAT TRANSFER EXPERIMENTS ON TURBINE BLADE[J]. Journal of Aerospace Power, 1987, 2(1): 18-22,89.

PDF( 521 KB)

APPLICATION OF SHOCK TUNNEL TO HEAT TRANSFER EXPERIMENTS ON TURBINE BLADE

Institute of Mechanics, Academia sinica

Received Date: 1986-07-01
Publish Date: 1987-01-28

Abstract

Abstract

Transient wind tunnels and their supplementary instrumentation have been used to examine the flow and heat transfer around hypersonic vehicles. The purpose of this paper is to describe their application to turbine cascade testing and refinements of its heat transfer measurement techniques.