RESULTS OF A SPACE SHUTTLE VEHICLE FERRY CONFIGURATION AFTERBODY FAIRING OPTIMIZATION STUDY USING A 143A/B 0.O405-SCALE MODEL ORBITER (43-0) IN THE ROCKWELL INTERNATIONAL 7.75 X 11.0 FT LOW SPEED WIND TUNNEL (0A124)

摘要

Experimental aerodynamic investigations were conducted on a dual-strut mounted 0.0405-scale representation of the 140A/B outer mold line Space Shuttle Orbiter Vehicle in the Rockwell International 7.75 × 11.0 ft low speed wind tunnel (NAAL). Tests were conducted during the time period from 11 Oct. 1974 through 22 Oct. 1974. The facility test number was NAAL 736 and the NASA designation for this test period was 0A124.nThe primary test objective was to investigate aerodynamic stability and control characteristics of the SSV ferry configuration. Test objectives were accomplished by testing four afterbody fairing configurations and various additions to them in the form of horizontal and ventral fins strakes and other aerodynamic protuberances. Base line data on the basic Orbiter with MPS nozzles and bodyflap were recorded. A secondary test objective was to increase the drag of the optimum ferry configuration to the level of the basic Orbiter for possible flight test configurations. This was accomplished by the addition of two sizes of perforated speed brakes on the tail cone surface.