Subsonic, Transonic and Supersonic Wind Tunnel Tests of the Generic Slender Wing Configuration DLR-F22 with Leading-Edge Vortex Controllers and Strakes

Abstract

This report provides detailed information on four wind tunnel campaigns performed with the DLR-F22 model in the transonic wind tunnel DNW-TWG. Main purpose of the tests is to investigate the effect on the vortical flow field of the size of a LEVCON-strake combination arranged ahead of a slender wing. To this end, the DLR-F22 model was tested with six wing planforms differing in LEVCON span and strake length. The corresponding configurations are designated F22-LS1, F22-L05, F22-L03, F22-L00, F22-S05 and F22-S01. The configurations were tested at Mach numbers M = 0.5 – 2.0. On the lee side of the model, pressures were determined at surface pressure port sections thus providing an overview of the location of vortices and the position of their breakup. The normal force and the pitching moment were measured via strain gauges attached to the mounting sting. Angle-of-attack sweeps were performed at different angles of sideslip, and angle of sideslip sweeps at different angles of attack. A complete compilation of all tests is provided and results are briefly reviewed and exemplarily discussed.