Accession Number : ADA307162

Title :   Arc-Tunnel Evaluation of Some Ablative Heat Shield Materials for the X-15-2.

Descriptive Note : Technical note,

Corporate Author : NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HAMPTON VA LANGLEY RESEARCH CEN TER

Personal Author(s) : Chapman, Andrew J. ; Dow, Marvin B.

PDF Url : ADA307162

Report Date : FEB 1967

Pagination or Media Count : 108

Abstract : Fourteen ablation materials have been investigated at test conditions simulating the heating predicted for the X-15-2 research aircraft. Twenty-seven wedge-shaped models with a leading-edge radius similar to the X-15-2 wing and horizontal stabilizer leading edges were tested in the 2-inch supersonic arc tunnel at the Langley Research Center. The ablation materials were exposed to the heating conditions which will occur on the X-15-2 leading edges and fuselage areas at an altitude of 105,000 feet (32 kilometers) and at Mach number 8. The results presented include back surface temperature response at several locations on the models and photographs of the models before and after testing.

Descriptors :   *HEAT SHIELDS, *RESEARCH AIRCRAFT, *ABLATIVE MATERIALS, TEST AND EVALUATION, MODELS, COATINGS, HEATING, FUSELAGES, LEADING EDGES, SUPERSONIC FLOW, SURFACE TEMPERATURE, HORIZONTAL STABILIZERS.

Subject Categories : Miscellaneous Materials
      Research and Experimental Aircraft
      Coatings, Colorants and Finishes

Distribution Statement : APPROVED FOR PUBLIC RELEASE