EXPERIMENTAL AND THEORECTICAL INVESTIGATION OF THE NEAR WAKE IN AN AXISYMMETRIC SUPERSONIC FLOW WITH AND WITHOUT BASE INJECTION.
Final rept. 27 Jun 64-26 Jun 68,
NEW YORK UNIV N Y DEPT OF AERONAUTICS AND ASTRONAUTICS
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Results of an experimental and theoretical investigation of the near wake in an axisymmetric flow past a slender body at Mach number 3.92 with and without base injection are presented. For the experimental part centerline distributions of pressure, temperature, Mach number, velocity, and concentration were obtained. Turbulent as well as laminar flow fields were investigated for the zero injection case. Base injection problem was studied only in the turbulent flow case using gaseous hydrogen, helium, nitrogen, and argon as injectants. A special effort was made to study the variation of pressure, velocity, and Mach number at the base with base injection. For the theoretical part an expression was developed to calculate the centerline distribution of turbulent viscosity from experimental profiles using full Navier-Stokes equations flow fields with non-zero pressure gradients were considered. Using this expression, centerline viscosity distributions for various cases of wake flow and coaxial mixing were calculated and the results compared with those obtained from the empirical models. Author
- Fluid Mechanics