This report presents the results of a state-of-the-art study on pressure and heat-transfer distribuions 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. (Author)
A Critical Review of Data on Heat Transfer and Pressure Distribution on Nose Cones in the High Unit Reynolds Number Regime
1967
71 pages
Report
Keine Angabe
Englisch
Fluid Mechanics , Nose cones , Aerodynamic characteristics , State-of-the-art reviews , Conical bodies , Cylindrical bodies , Flared afterbodies , Supersonic characteristics , Hypersonic characteristics , Heat transfer , Pressure , Load distribution , Boundary layer transition , Turbulent boundary layer , Flow separation , Blunt bodies , Experimental data , Tables(Data) , Free flight models , Wind tunnel models , Reynolds number , Test facilities , Low altitude , Graphs(Charts) , Sharp bodies
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