SURFACE PRESSURE DISTRIBUTIONS ON A LARGE-SCALE 49°SWEPTBACK WING-BODY-TAIL CONFIGURATION WITH BLOWING APPLIED OVER THE FLAPS AND WING LEADING EDGE

摘要

An investigation has been conducted in the Langley full-scale tun¬nel to determine the pressure-distribution characteristics of a large-scale sweptback wing-body-tail configuration as affected by blowing air over highly deflected trailing-edge flaps in combination with several wing-leading-edge flow-control devices, including leading-edge blowing. The wing had an aspect ratio of 3.5 a taper ratio of 0.3, a leading-edge sweep of 49°, and NACA 65AOO6 airfoil sections parallel to the plane of symmetry. The tests were conducted over a range of angles of attack, flap angles, and aileron angles. The range of Momentum coefficients for flap and leading-edge blowing varied from 0 to O.I87 and from 0 to 0.034,nrespectively. The Reynolds number of the tests was 5.2 x 106, corre-sponding to a Mach number of 0.08.