Counterflow Injection Studies for Hypersonic Flow Fields
Hypersonic vehicles invariantly face the problem of higher wave drag and surface heat transfer rate. These problems increase proportionally with increase in speed in this flow regime. Counter-flow injection from stagnation point is one of the remedies for this problem. Possibility of implementation and active control mechanism are advantages of counter-flow drag reduction (CDR) technique. Numerous investigations like effect of Mach number, Reynolds number, injection pressure, coolant gas, stagnation enthalpy etc.are the outcome of active research in the field of CDR studies.
KeywordsMach Number Stagnation Point Drag Reduction Hypersonic Flow Hypersonic Vehicle
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