Modeling trans- and supersonic viscid flow over a cone on a ballistic range

摘要

The possibilities of ballistic-range experimentation in determining the influence of compressibility and viscosity on the flow over cone-shaped parts of flying vehicles are considered. A nonmonotonic character of the dependence of the near wake flow over cone on the Reynolds number is revealed, which is an important factor under natural flight conditions. Tests have been performed for a right circular cone with a half-angle of 15. The drag coefficients (C-x) for acute and blunt cones with an aspect ratio of L/D = 1 at a zero attack angle have been determined. Near wake flow parameters (base pressure rho(b) and base density rho b) have been experimentally studied in a range of Mach numbers M-infinity = 0.5-4 and at a fixed value of M-infinity = 2.3, but with Reynolds numbers Re-infinity D varied from 6 x 10(4) to 1.5 x 10(6).