Abstract
An effective control strategy is studied in this work to reduce aerodynamic heating inside transitional hypersonic boundary layers, which is of both scientific significance and practical importance. The experiments show that the use of grooved wavy walls covered with an acoustic transparent film can successfully reduce the growth of Mack's second mode, which delays transition and results in significant reduction of aerodynamic heating.
Funder
National Natural Science Foundation of China
National Key Project
Subject
Condensed Matter Physics,Fluid Flow and Transfer Processes,Mechanics of Materials,Computational Mechanics,Mechanical Engineering
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