TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
Online ISSN : 2189-4205
Print ISSN : 0549-3811
ISSN-L : 0549-3811
Studies on the Effects of Test Gas on the Flow Field around Large Angle Blunt Cone Flying at Hypersonic Mach Number
Gopalan JagadeeshKanderpallt NagashettyK. P. Jaganntha ReddyMingyu SunKazuyoshi Takayama
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2002 Volume 45 Issue 149 Pages 189-194

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Abstract

The effect of the test gas on the flow field around a 120° apex angle blunt cone has been investigated in a shock tunnel at a nominal Mach number of 5.75. The shock standoff distance around the blunt cone was measured by an electrical discharge technique using both carbon dioxide and air as test gases. The forebody laminar convective heat transfer to the blunt cone was measured with platinum thin-film sensors in both air and carbon dioxide environments. An increase of 10 to 15% in the measured heat transfer values was observed with carbon dioxide as the test gas in comparison to air. The measured thickness of the shock layer along the stagnation streamline was 3.57±0.17 mm in air and 3.29±0.26 mm in carbon dioxide. The computed thickness of the shock layer for air and carbon dioxide were 3.98 mm and 3.02 mm, respectively. The observed increase in the measured heat transfer rates in carbon dioxide compared to air was due to the higher density ratio across the bow shock wave and the reduced shock layer thickness.

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© 2002 The Japan Society for Aeronautical and Space Sciences
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