Accession Number : AD0462332


Title :   EQUILIBRIUM, ADIABATIC WALL, AND STAGNATION TEMPERATURES AT ALTITUDES UP TO 100,000 FEET AND MACH NUMBERS UP TO 20


Descriptive Note : Technical memo.


Corporate Author : JOHNS HOPKINS UNIV LAUREL MD APPLIED PHYSICS LAB


Personal Author(s) : Suess, R P ; Weckesser, L B


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/462332.pdf


Report Date : Dec 1964


Pagination or Media Count : 104


Abstract : In the preliminary design phase of high velocity vehicles, quick, conservative estimates of surface temperatures are always desirable. To fill this need, the equilibrium, adiabatic wall, and stagnation temperatures have been determined for altitudes from sea level to 100,000 feet and for Mach numbers from 2 to 20. Data for both laminar and turbulent flow are presented. For easy reading, the results are presented as temperature versus Mach number plots at altitude intervals of 10,000 feet. The only information necessary to obtain equilibrium temperatures from this report is: distance from the leading edge to the point in question, emissivity of the surface, Mach number, and altitude.


Descriptors :   *HYPERSONIC AIRCRAFT , *FLAT PLATE MODELS , HEAT TRANSFER , TURBULENCE , TURBULENT BOUNDARY LAYER , HIGH ALTITUDE , HYPERSONIC CHARACTERISTICS , STAGNATION POINT , LAMINAR BOUNDARY LAYER , LOW ALTITUDE , UPPER ATMOSPHERE , SUPERSONIC CHARACTERISTICS , SURFACE TEMPERATURE , LAMINAR FLOW , AERODYNAMIC HEATING


Subject Categories : Research and Experimental Aircraft


Distribution Statement : APPROVED FOR PUBLIC RELEASE