Compressible Boundary Layer Receptivity and Instability
Final rept. 1 Dec 1998-31 Aug 1999
PRINCETON UNIV NJ DEPT OF MECHANICAL AND AEROSPACE ENGINEERING
Pagination or Media Count:
A high quality flow has been established in a low turbulence variable geometry LTVG 8 x 8 supersonic wind-tunnel at Princeton. In particular, the facility is being operated at very low stagnation pressures - 4 psia giving a large region of laminar flow on a flat plate with laminar boundary layers up to approximately 3rnm thick. Mean profiles, amplitude distributions, two wire correlations and spectra have been mcasured in detail through a Mach 3 boundary layer along the centerline of the flat plate. The initial results are for naturally occurring instability and transition and they are being followed by measurements of the forced response from a point source spark .1.
- Fluid Mechanics