SCALING EFFECTS ON SHOCK-BOUNDARY LAYER INTERACTION IN TRANSONIC FLOW

Experiments were conducted to determine the effects of unit Reynolds number and boundary layer condition on shock-boundary layer interaction and the subsequent flow development for simulated airfoil contours. Tests were made with three circular-arc, half-thickness models mounted on the tunnel floor....

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Bibliographische Detailangaben
Hauptverfasser:	Stanewsky,E, Hicks,J G
Format:	Report
Sprache:	eng
Schlagworte:	Aircraft AIRFOILS BOUNDARY LAYER DATA PROCESSING FLAT PLATE MODELS Fluid Mechanics INTERACTIONS MATHEMATICAL MODELS MODEL TESTS NOZZLE GAS FLOW REYNOLDS NUMBER S/L change 8312 SCALE SHOCK WAVES THICKNESS TRANSONIC CHARACTERISTICS WEDGES WIND TUNNEL MODELS
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