FREE-FLIGHT MEASUREMENT OF LOCAL TURBULENT SKIN FRICTION ON AN RM-10 VEHICLE.
TEXAS UNIV AUSTIN DEFENSE RESEARCH LAB
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In-flight skin-friction measurements were made on an RM-10 rocket test missile. A floating-element, direct-measuring skin friction balance and a surface impact probe were used. The balance performance was questionable because of errors induced by the shock of booster and sustainer rocket ignition. The impact probe method gave satisfactory results including flight times where aerodynamic heating occurred, but the results were at times influenced by angle-of-attack effects. The balance and probe data were found to agree satisfactorily with the Van Driest theory for skin friction on a flat plate with heat transfer except when the missile was at angle of attack, for which times the theory is not applicable. Recommendations for instrumentation refinements are included. Author
- Test Facilities, Equipment and Methods
- Fluid Mechanics