AILERON AND KRUGER NOSE FLAP EFFECTIVENESS MEASURED ON AN OBLIQUE WING

摘要

The effects that deflection of conventional ailerons have on the lateral/directional characteristics of an oblique wing mounted on top of a body of revolution were measured The wing had an aspect ratio of 6 (based on the unswept wing span) and was tested at various sweep angles ranging from 0° to 60° Kruger nose flaps mounted on drooped-nose flaps were investigated on the downstream wing panel (for sweep angles of 45° and 60°) in an attempt to create more symmetrical spanwise wing stalling at high lift coefficients The tests were conducted over a Mach number range of 0 25 to 1 4 and an angle-of-attack range from -3° to 28°nWith the oblique wing in the swept position, considerable difference in the aileron effectiveness was measured for positive or negative differential aileron deflections With the wing swept 45° at a Mach number of 0 8 and above, an extension of the span of the Kruger nose flaps on the downstream wing panel did not improve the linearity of the pitching-, rolling-, and yawing-moment curves.