Investigation of Test Facility Environmental Factors Affecting Boundary Layer Transition.
Technical rept. Sep 71-Jul 73,
AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OHIO
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Tests were conducted on the sidewall boundary layer of a 4-inch I.D. shock tube over a shock Mach number range 3 to 15 and unit Reynolds number range of 500000 per foot to 4000000 per foot. Effects of facility environments, measured with accelerometers and microphones, were correlated with boundary layer transition Reynolds numbers and other flow parameters such as the boundary layer cooling ratio, static and dynamic pressures and local flow Mach number. At a fixed unit Reynolds number a multiple reversal transition Reynolds number curve was and dynamic pressures and local flow Mach number. At a fixed unit Reynolds number a multiple reversal transition Reynolds number curve was found as a function of wall cooling. Also, spectral content of wall and acoustic fluctuations was found to correlate with transition Reynolds number for a discrete set of frequencies. Author
- Fluid Mechanics