Laminar Instability and Transition on the X-51A
PURDUE UNIV LAFAYETTE IN SCHOOL OF AERONAUTICS AND ASTRONAUTICS
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A 20 scale model of the X-51A forebody was tested in the BoeingAFOSR Mach-6 Quiet tunnel. Freestream noise was found to have a major impact on transition on the windward and leeward vehicle surfaces. The effect of noise on transition was observed with a smooth wall and for roughness-induced transition on both surfaces. Temperature sensitive paint TSP and hot wires were used to characterize transition onset on the windward surface. The transition Reynolds number Ret increased by a factor of at least 2.2 for a smooth wall, 2.4 with ramp roughnesses, and 1.7 for diamond roughnesses when the freestream noise was decreased.
- Research and Experimental Aircraft
- Test Facilities, Equipment and Methods
- Fluid Mechanics