PRELIMINARY STUDIES OF THE FLOW AROUND TWO-DIMENSIONAL BODIES AT HIGH MACH NUMBERS AND LOW REYNOLDS NUMBERS.
Scientific interim rept.,
PRINCETON UNIV N J GAS DYNAMICS LAB
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The studies were primarily concentrated on the leading edge region where the shock wave and the viscous region caused by the body itself interact. The studies were carried out at a Mach number of about 24. In a hot nitrogen wind tunnel operating at stagnation pressures of 2000-5000 lbsq.in. and at stagnation temperatures to 2700 K., results were obtained for values of the interaction parameter from 60-250. In this region, results were obtained on a flat plate with leading edge thicknesses which varied from a fraction of a mean free path to hundreds of mean free paths. The detailed pressure distributions obtained over the body seemed to indicate significant deviations from the strong interaction theory, falling considerably below the theoretical results. Exploratory studies of the details of the flow field in this region indicate that the simple one-dimensional Rankine-Hugoniot equations cannot be used across the shock wave. A new tool for study of this region indicates shock profiles which show the changes in the structure of the phenomenon as one approaches the leading edge. Author
- Fluid Mechanics