Effect of Reynolds number on the subsonic boattail drag of several wing-body configurations
David E. Reubush, Langley Research Center, United States. National Aeronautics and Space Administration
U.S. National Aeronautics and Space Administration, 1976 - Science - 82 pages
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1/3-meter transonic cryogenic Adcock aft position AIAA Paper angle of attack attack at Mach boattail became Boattail pressure coefficient boattail pressure drag boattail static boattail static-pressure coefficients boattail with wing circular-arc boattail circular-arcóconic boattail Concluded cone-cylinder nacelle models Continued D.deg delta wing distributions at various Effect of Reynolds expansion region Figure 17 Figure 9 Flight Test forward position High Reynolds Number investigation was conducted isolated boattails Kilgore Langley 1/3-meter transonic Langley Research Center large interference effects Mach numbers middle position model maximum diameter NASA TN number on boattail number was increased numbers from 0.6 O.deg operating the tunnel pressure coefficient distributions Pressure Drag Coefficients result Reubush Reynolds number variation series of isolated stagnation pressures stagnation temperatures STATIC PRESSURE ORIFICE sting transonic cryogenic tunnel tunnel at stagnation various Reynolds numbers wind-tunnel Wing in aft wing in forward wing in middle WING-BODY CONFIGURATIONS x/dm xlO6