Documented are representative photographs of surface flow patterns, created by oil flow and shadowgraph techniques, obtained during wind tunnel tests of an 0.004-scale version of the 2A SSV orbiter. The purpose of this test series was to obtain flow visualization photographs to aid in interpretation of test IS1 aero-noise data. The test was conducted at nominal Mach numbers from 0.6 to 3.48. The orbiter was run in proximity to the external tank and solid rocket boosters at angles of attack from -5 deg to +9 deg at 0 deg angle of sideslip. (Author)
Flow Visualization Tests of a 0.004-Scale Space Shuttle Vehicle 2A Model (No. 13-Ots) in the Msfc 14-Inch Trisonic Wind Tunnel (Is6a)
1976
37 pages
Report
Keine Angabe
Englisch
Uncertainty Analysis of the NASA MSFC 14-Inch Trisonic Wind Tunnel
British Library Conference Proceedings | 1999
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