The results of hypersonic wind tunnel testing of an 0.0175 scale version of the vehicle 3 space shuttle configuration are presented. Temperature measurements were made on the launch configuration, orbiter plus tank, orbiter alone, tank alone, and solid rocket booster alone to provide heat transfer data. The test was conducted at free-stream Mach numbers of 5.3 and 7.3 and at free-stream Reynolds numbers of 1.5 million, 3.7 million, 5.0 million, and 7.0 million per foot. The model was tested at angles of attack from -5 deg to 20 deg and side slip angles of -5 deg and 0 deg. (Author)


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    Title :

    Hypersonic Aeroheating Test of Space Shuttle Vehicle Configuration 3 (Model 22-Ots) in the NASA-Ames 3.5-Foot Hypersonic Wind Tunnel (IH20), Volume 1


    Contributors:

    Publication date :

    1975


    Size :

    791 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English