Accession Number : ADA130031

Title :   Wind Tunnel Tests of Space Shuttle Solid Rocket Booster Insulation Material in the Aerothermal Tunnel C.

Descriptive Note : Final rept. 2-22 Sep 82,

Corporate Author : ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFS TN

Personal Author(s) : Hartman,A S ; Nutt,K W

PDF Url : ADA130031

Report Date : Nov 1982

Pagination or Media Count : 55

Abstract : For these wind tunnel tests, conducted in the von Karman Gas Dynamics Facility Tunnel C, the tunnel was run at Mach 4 with a total temperature of 1100-1440 F and a total pressure of 100 psia. Cold wall heating rates were changed by varying the test article support wedge angle. Selected results are presented to illustrate the test techniques and typical data obtained.

Descriptors :   *Thermal insulation, Propellant tanks, Aerodynamic heating, Wind tunnel tests, Space shuttles, Booster rocket engines, Foam, Heat transfer, External, Infrared images, Hypersonic wind tunnels

Subject Categories : Miscellaneous Materials
      Test Facilities, Equipment and Methods
      Unmanned Spacecraft

Distribution Statement : APPROVED FOR PUBLIC RELEASE