Accession Number : AD0274578

Title :   INVESTIGATION OF VORTEX MOVEMENTS ABOUT WING IN INTERMEDIATE AND HIGH SUBSONIC FLOW UNDERGOING A LARGE ANGLE-OF-ATTACK CHANGE IN A BLAST-INDUCED GUST

Corporate Author : NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON D C

Personal Author(s) : MCFARLAND,DONALD R.

Report Date : APR 1962

Pagination or Media Count : 1

Abstract : Measurements were made of the vortex movements about an airfoil undergoing a blast of sufficient strengt to exceed momentarily the stall angle by a large amount. This report extends the previously reported low-speed data to the intermediateAND HIGH SUBSONIC VELOCITIE . A heated shockdriven tunnel was used to provide a high subsonic, steady, free jet of short duration to simulate the model flight. Small high-explosive charges were used to produce scaled blast waves. Generally, the trailing-edge vortices travel at the fluid stream velocities, whereas leading-edge vortices travel at lower speeds. Comparison of a modified Rott theory and vortex data produced by the blast wave alone shows less agreement at the higher velocities than the low-speed data previ usly reported. The results indicate that the identity of the leading-edge vortex is lost in the presence of the supercritical flow over the wing model. (Author)

Descriptors :   *VORTICES, *WINGS, AERODYNAMIC CHARACTERISTICS, AIRFOILS, BLAST, GUSTS, MODEL TESTS, SHOCK WAVES, STALLING, SUBSONIC FLOW, TRANSONIC CHARACTERISTICS, WIND TUNNEL MODELS

Distribution Statement : APPROVED FOR PUBLIC RELEASE