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>The Experimental Measurement of Aerodynamic Heating About Complex Shapes at Supersonic Mach Numbers
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The Experimental Measurement of Aerodynamic Heating About Complex Shapes at Supersonic Mach Numbers
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机译:超音速马赫数复杂形状气动加热的实验测量
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摘要
In 2008 a wind tunnel test program was implemented to update the experimental data available for predicting protuberance heating at supersonic Mach numbers. For this test the Langley Unitary Wind Tunnel was also used. The significant differences for this current test were the advances in the state-of-the-art in model design, fabrication techniques, instrumentation and data acquisition capabilities. This current paper provides a focused discussion of the results of an in depth analysis of unique measurements of recovery temperature obtained during the test.
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