Accession Number:

ADA504178

Title:

Laminar Instability and Transition on the X-51A

Descriptive Note:

Doctoral thesis

Corporate Author:

PURDUE UNIV LAFAYETTE IN SCHOOL OF AERONAUTICS AND ASTRONAUTICS

Personal Author(s):

Report Date:

2009-08-01

Pagination or Media Count:

169.0

Abstract:

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.

Subject Categories:

  • Research and Experimental Aircraft
  • Test Facilities, Equipment and Methods
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE