PRELIMINARY INVESTIGATION OF THE INTERACTION OF AN OBLIQUE SHOCK WAVE AND A TURBULENT BOUNDARY LAYER
A continuous, two-dimensional, M = 2.5, wind tunnel with a one-inch squsre test section was modified to include a boundary layer probe and a shock- wave generating wedge. The point of incidence of the 29-degree shock wave was moved horizontally relative to the wall taps and the probe in the upper tunnel wall by moving the wedge vertically. Probe surveys were made upstream, in the middle, and downstream of the interaction of the shock wave and the turbulent boundary layer. The wall static pressures were measured with each probe survey. An investigation was made of the theory to determine the limitations of the approximate boundary layer equations. A theory for partially describing the interaction of turbulent boundary layers without flow separation was studied. The boundary layer upstream of the interaction had a boundary layer, displacement, and momentum thickness of 0.085, 0.0235, and 0.00619 inches, respectively. Its Reynolds number based on the effective length of the turbulent boundary layer was 7.2 x 10/sup 5/. The ratio of the downstream to upstream boundary layer thickness was 0.83. (auth)
- Research Organization:
- New Mexico. Univ., Albuquerque
- NSA Number:
- NSA-15-024947
- OSTI ID:
- 4021917
- Report Number(s):
- SCTM-146-61(13)
- Resource Relation:
- Other Information: For Sandia Corp. Orig. Receipt Date: 31-DEC-61
- Country of Publication:
- United States
- Language:
- English
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