Book Description

A high Reynolds number test of a 5 percent thick low aspect ratio semispan wing was conducted in the adaptive wall test section of the Langley 0.3 m Transonic Cryogenic Tunnel. The model tested had a planform and a NACA 64A-105 airfoil section that is similar to that of the pressure instrumented canard on the X-29 experimental aircraft. Chordwise pressure data for Mach numbers of 0.3, 0.7, and 0.9 were measured for an angle-of-attack range of -4 to 15 deg. The associated Reynolds numbers, based on the geometric mean chord, encompass most of the flight regime of the canard. This test was a free transition investigation. A summary of the wing pressures are presented without analysis as well as adapted test section top and bottom wall pressure signatures. However, the presented graphical data indicate Reynolds number dependent complex leading edge separation phenomena. This data set supplements the existing high Reynolds number database and are useful for computational codes comparison. Chu, Julio and Lawing, Pierce L. Langley Research Center BOUNDARY LAYER SEPARATION; HIGH REYNOLDS NUMBER; LOW ASPECT RATIO WINGS; PRESSURE DISTRIBUTION; WIND TUNNEL TESTS; WING LOADING; AIRFOIL PROFILES; CANARD CONFIGURATIONS; COMPUTATIONAL FLUID DYNAMICS; CRYOGENIC WIND TUNNELS; LEADING EDGES; SUBSONIC SPEED; TRANSONIC WIND TUNNELS; WALL PRESSURE; X-29 AIRCRAFT...