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).
Static Force and Moment Test of the Holloman Narrow-Gage Rocket Sled at Mach Numbers from 3.5 to 5.5
1987
48 pages
Report
No indication
English
Rockets , Rocket sleds , Aerodynamic loading , Aerodynamics , Air force facilities , Analyzers , Angle of attack , Assembly , Experimental data , Ground level , Image processing , Information systems , Mach number , Moments , Rails , Rocket engines , Scale models , Static loads , Supersonic wind tunnels , Variables , Wedges , Wind tunnel tests , Supersonic characteristics , Tracks(Aerodynamics) , Tables(Data) , IADS(Image Analyzer Data System) , Narrow gage rocket sleds