NEWTONIAN THEORY FOR THE STAGNATION REGION OF TWO OPPOSING HYPERSONIC STREAMS

It is proposed that the zone of interaction between two opposing hypersonic streams can be described in terms of a thin layer of compressed gases bounded on either side by shock waves. Newtonian flow theory is used to analyze the interaction when one of the streams corresponds to the exhaust gas flo...

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Bibliographische Detailangaben
1. Verfasser:	Laurmann,John A
Format:	Report
Sprache:	eng
Schlagworte:	AERODYNAMIC LOADING ATMOSPHERE ENTRY EXHAUST GASES FLOW FIELDS Fluid Mechanics HYPERSONIC CHARACTERISTICS INTERACTIONS NOZZLE AREA RATIO NOZZLE GAS FLOW NOZZLE THROATS NUMERICAL ANALYSIS PLASMA SHEATHS REENTRY VEHICLES SHOCK WAVES Spacecraft Trajectories and Reentry STAGNATION POINT
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