Data Verification Tests of a 0.03-Scale NASA Space Shuttle Launch Vehicle at Mach Numbers from 0.60 to 1.55.
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFS TN
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A 0.03-scale model of the NASA Space Shuttle Launch Vehicle was tested September 19-20 and September 29-30, 1978, in the Propulsion Wind Tunnel 16T at free-stream Mach numbers from 0.60 to 1.55, free-stream dynamic pressures from 387 to 658 psf, angles of attack from -8 to 8 deg, angles of sideslip from -6 to 6 deg, and roll angles of 0, 180, 90, and -90 deg with nominal inboard elevon deflections of 10 deg and outboard elevon deflections of 5 deg. The objectives of the test were to determine flow angularity on the standard sting support system first entry and high-pitch support system second entry, and to provide data throughout an alphabeta matrix to establish a data base for the determination of angular corrections to be applied to previously obtained data if such corrections are necessary. Author
- Unmanned Spacecraft
- Spacecraft Trajectories and Reentry