LOW-SPEED WIND-TUNNEL INVESTIGATION OF A LARGE SCALE ADVANCED ARROW-WING SUPERSONIC TRANSPORT CONFIGURATION WITH ENGINES MOUNTED ABOVE WING FOR UPPER-SURFACE BLOWING

摘要

Tests have been conducted in the Langley full-scale tunnel to determine the low-speed aerodynamic characteristics of a large-scale advanced arrow-wing supersonic transport configuration with engines mounted above the wing for upper-surface blowing. Tests were made over an angle-of-attack range of -10° to 32°, sideslip angles of ±5°, and a Reynolds number range of 3.53 x 106 to 7.33 x 106 (referenced to mean aerodynamic chord length of 3.368 m (11.050 ft) of the wing). Configuration variables included trailing-edge flap deflec¬tion, engine jet-nozzle angle, engine thrust coefficient, engine-out operation, and asym¬metrical trailing-edge boundary-layer control for providing roll trim. Downwash measure¬ments at the tail were obtained for different thrust coefficients, tail heights, and at two fuselage stations.