RESULTS OF INVESTIGATION IA110 ON A 0.015-SCALE INTEGRATED CONFIGURATION OF THE SPACE SHUTTLE VEHICLE IN THE ARC 9 x 7 SUPERSONIC HIWD TUNNEL USING MODELS 67-TS AND 49-0

摘要

Results of test IA110 are presented in this report. An 0.015-scale Space Shuttle Vehicle model was tested 1n the Ames Research Center 9×7 Supersonic wind Tunnel during July 1974 to investigate Orbiter wing bending, elevon panel loads, and elevon effectiveness. Mach numbers from 1.5 through 2.5 were investigated. Angles of attack and sideslip were varied from -8 degrees through +8 degrees.nPost test analysis of raw wind tunnel data Indicated a zero shift had occurred in the wing bending and torsional gages during the test. The mechanism by which this shift occurred was not determined. Therefore, all the wing root bending and torsional moment data 1s suspect.nData figure 18 presents comparisons with data from test IA70 (DMS-DR-2175). The same model and Instrumentation was used for both bests.