Abstract
The aerodynamic interaction flow field between a delta wing and a hemisphere-cylinder modeling TSTO (Two Stage To Orbit) in hypersonic flow has been investigated. The paint method for visualization has been improved in order to perform temperature distribution measurements by the Temperature Sensitive Paint (TSP) method, where pressure sensitivity has been reduced by recoating a transparent acrylic paint. The flow field is made complicated by both shock/shock interaction and shock/boundary layer interaction. On the hemisphere-cylinder, the maximum heat flux becomes about 2.7 times as large as the stagnation heat flux in the case of a hemisphere-cylinder alone. On the other hand, the same amount of heat flux as that stagnation value is produced on the delta wing located below the tip of the hemisphere-cylinder.
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