Lee Surface Flow over Delta Wings at Supersonic Speeds: Some Features of Different Types of Flow

摘要

The features of the different types of flow on the lee surface of delta wings at supersonic speeds were studied in terms of the location of separation and re-attachment lines and shock waves and their variation with Mach number, sweep back, thickness, and angle of attack. The study is largely based on tests on two sets of flat topped delta wing models having sweep back angles of 45, 50, 60, and 70 degrees at freestream Mach numbers of 1.6, 1.8, 2.0, 2.5, and 3.0. The first set of models had a wedge angle normal to the leading edge of 10 degrees while the second set had a wedge angle of 25 degrees. In addition, a 60 degree sweepback delta wing with a wedge angle of 40 degrees was also tested. The results indicate that in the leading edge separated flow region, the location of attachment and secondary separation lines and their variation with the angle of attack depended on the particular type of flow. In the attached leading edge flow region, however, the location of the shock-induced separation line is independent of the particular type of flow. Within each type of flow, the effects of thickness are in general found to be small.