A Critical Review of Data on Heat Transfer and Pressure Distribution on Nose Cones in the High Unit Reynolds Number Regime

摘要

The report presents the results of a state-of-the-art study on pressure and heat-transfer distributions on axisymmetric bodies in the high Reynolds number per foot regime. The Mach number range covered is generally from 3.5 to 9 corresponding to the flight envelope of the Army Missile Command low-altitude/high-velocity experiment (LAHIVE). In addition to a summary of previous flight and wind-tunnel data, areas of controversy and unexplained or anomalous results are pointed out in which LAHIVE data will be of great value. A brief survey is presented of Government-owned wind tunnels, ranges, and shock tunnels pertinent to the LAHIVE flight regime. Recommendations on instrumentations are included, particularly for the cone-cylinder-flare vehicles, on the data analysis and correlation of results, and on further applications of LAHIVE vehicles.