The results are presented of a flow-visualization wind tunnel test of a 0.015-scale model of the Modified Configuration 140A/B Space Shuttle Vehicle Orbiter. Separation zones, flow-recirculation regions, and potential venting and contaminant-ingestion problem areas were studied by means of photographic (video tape) analysis of model-mounted tufts. The model was tested at Mach numbers of 0.60, 0.90, 1.05, and 1.20, at Reynolds numbers of 3.17, 3.98, 4.16, and 4.23, respectively. Model angle-of-attack was varied from 0 deg to 20 deg at 0 deg sideslip-angle. Three control-surface deflection combinations were tested. (Author)
Results of Flow-Visualization Investigations on a 0.015-Scale Modified Configuration 140A/B Space Shuttle Vehicle Orbiter (Model 36-0) in the Langley Research Center 8-Foot Transonic Pressure Tunnel (OA102)
1975
25 pages
Report
No indication
English