Effect of Shock Wave/Boundary Layer Interaction on Reservoir Temperature in Shock Tunnel

Author:

Kaneko Munetsugu,Nakamura Yoshiaki

Publisher

Japan Society for Aeronautical and Space Sciences

Reference17 articles.

1. 1) 中北和之:衝撃風洞における空気力及び空力加熱率の測定法について,名古屋大学修士論文,1993.

2. Three-Dimensional Shock/Boundary-Layer Interaction Between a Rocket and a Booster

3. 3) Gaydon, A. G.: The Shock Tube in High Temperature Chemical Physics, Chapman and Hall, London, 1963.

4. Driver gas contamination in a high-enthalpy reflected shock tunnel

5. 5) Prodromou, P. and Hillier, R.: Computation of Unsteady Nozzle Flows, Proc. of the 18th Intl. Symp. on Shock Waves, 1991.

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1. Aerodynamic Heating of a Gap in the Hypersonic Laminar Boundary Layer;TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN;2013

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3. Aerodynamic Heating Due to Interaction between Boundary Layer Reattachment and Rectangular Cavity in Hypersonic Compression Ramp;JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES;2011

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