THE AERODYNAMIC CHARACTERISTICS OF A 75-DEG SWEPT DELTA WING AT HIGH ANGLES OF ATTACK AND MACH NUMBERS OF 2 TO 8 (U)
ARO INC ARNOLD AFS TN
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An experimental investigation was conducted in a 12 in. supersonic tunnel and a 50 in. Mach 8 tunnel to determine the aerodynamic characteristics of a delta wing at high angles of attack. The configuration tested was a flat, blunt leading edge, delta wing with 75 degree sweepback. The tests were conducted at angles of attack from 30 to 105 degree and Mach numbers of 2, 3, 5, and 8. Longitudinal stability and drag characteristics, surface pressure distributions, and shock wave shapes are presented with theoretical estimates based on the Newtonian theory.
- Fluid Mechanics