Experimental aerodynamic investigations were conducted on a .006 scale model of the space shuttle 040-A orbiter and its external fuel tank utilizing the NASA/MFSC dual sting support system in the MFSC 14 x 14 inch Trisonic Wind Tunnel. Normal force, pitching moment and axial force components were recorded simultaneously on the orbiter and the tank at selected tank field positions beneath the orbiter as both models were pitched through an angle of attack range of -5 deg to 20 deg. Incidence angles between orbiter and tank of 0 deg, 5 deg, 10 deg and 15 deg were investigated. During these tests Mach number was set at 0.6, 2.0 and 4.0. (Author)
Abort Staging Characteristics of an External Oxygen Tank Separating from the Space Shuttle 040-A Orbiter (.006 Scale Model) at Mach Numbers of 0.6, 2.0, AND 4.0
1972
167 pages
Report
Keine Angabe
Englisch