Lee-Surface Flow over Delta Wings at Supersonic Speeds

摘要

Experiments were conducted to study the types of flow that occur on the lee surface of delta wings at supersonic speeds. Two sets of flat topped delta wings of different thickness, each with leading edge sweep angles of 45, 50, 60, and 70 degrees, were tested. The measurements, performed at Mach numbers of 1.4, 1.6, 1.8, 2.0, 2.5, and 3.0, included oil flow visualization and static pressure distributions. From these and other existing measurements, the leeside flows were classified into nine distinct types. These types of flows were displayed in a plane of Mach number and angle of attack normal to the leading edge. The experimental results indicate that increasing wing thickness has no qualitative effect on the types of flow observed but does shift the boundaries between some of the types of flow. The extensive static pressure data obtained has made it possible to identify each type of flow with a characteristic pressure distribution. The development of the flow as it changes from a leading edge separated type to an attached flow and vice versa was discussed based on the pressure distributions.