Tests of Vortex Generators to Prevent Separation of Supersonic Flow in a Compression Corner.

摘要

Tests were made on four vortex generators to determine their ability to prevent flow separation. The generators were of rectangular planform with chord lengths of 0.5and 1.0in. and spans of 0.25and 0.50in. Generator section shape was a symmetric double wedge. The generators were individually mounted at a 15deg angle of attack on a flat plate upstream of a 35deg compression corner. The tests were made in a wind tunnel at an average Mach Number of 4.67. The boundary layer was turbulent and approximately 1/4in. thick at the test station. Static pressure measurements were taken along the centerline of the plate and on the ramp face. Oil and dye flows and schlieren photographs were used to aid in determining the extent of separation.