Accession Number : AD0460484


Title :   ADVANCED X-15A-2 ABLATION SYSTEM DESIGN, TESTS, AND ANALYSIS


Descriptive Note : Technical Report,13 May 1963,07 Feb 1964


Corporate Author : NORTH AMERICAN AVIATION INC LOS ANGELES CA LOS ANGELES United States


Personal Author(s) : Johnson,Robert H ; Paxson,P O ; Bodne,J B ; Shatzkin,H


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/460484.pdf


Report Date : 16 Feb 1965


Pagination or Media Count : 183


Abstract : An investigation of ablation materials was conducted for application to an advanced, Mach 8 modification of the X-15 Research Airplane. Performance of the selected material, thermo-lag T-500, was evaluated in plasma tunnel tests and in flight tests. Estimates were made of required ablator weight and thicknesses at stagnation and non-stagnation areas of the Advanced X-15A-2. Performance data, resulting from actual flight tests, plasma tunnel tests and analytical predictions, were compared.


Descriptors :   HEAT RESISTANT MATERIALS , ROCKET AIRCRAFT , ABLATION , AERODYNAMIC HEATING , HYPERSONIC FLIGHT , RESEARCH AIRCRAFT , FLIGHT TESTING , MODEL TESTS , WIND TUNNEL MODELS , PERFORMANCE(ENGINEERING) , WEIGHT , THICKNESS , FLAT PLATE MODELS , HEAT SHIELDS , FUSELAGES , SHOCK WAVES , AIRCRAFT PROTUBERANCES , HEAT TRANSFER , LANDING GEAR , NOSE WHEELS , TEMPERATURE , EXPERIMENTAL DATA , TABLES(DATA)


Distribution Statement : APPROVED FOR PUBLIC RELEASE