A static force and moment test was performed in the Supersonic Wind Tunnel A at Mach numbers from 3.5 to 5.5 to obtain experimental aerodynamic data on the 1/12th scale model of a Narrow-Gage Rocket Sled. The test was performed with the model in close proximity to a ground plane and rail assembly simulating the High Speed Test Track at Holloman Air Force Base. The configuration variables were the mounting of either a 4 or 16-degree wedge above the rocket motors. Final tabulation of test data results are included in this report. Keywords: Aerodynamic loading; Rocket sled scale models; Wedges; Angle of attack; Wind tunnel test; Image Analyzer Data System(IADS).


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite