FLOW VISUALIZATION STUDIES OF A GENERAL RESEARCH FIGHTER MODEL EMPLOYING A STRAKE-WING CONCEPT AT SUBSONIC SPEEDS

摘要

A systematic wind-tunnel study was conducted in the Langley high-speed 7- by 10-foot tunnel to document, by oil-flow photographs, the surface flow patterns for config¬urations incorporating strake-wing geometries indicative of current and proposed maneuvering aircraft. The configurations employed combinations of strakes with reflexed planforms having exposed spans of 10 percent, 20 percent, and 30 percent of the reference wing span and wings with trapezoidal planforms having leading-edge sweep angles of approximately 30°, 44°, and 60°. Tests were conducted at Mach num¬bers of 0.3 and 0.5 and at angles of attack ranging from approximately 5° to 30° in 5° increments at 0° sideslip. The configurations incorporating the strake-wing geometries exhibited more organized flow patterns with smaller asymmetries to higher angles of attack than the corresponding configurations incorporating the wing-alone geometries did.