Possible types of flow on lee-surface of delta wings at supersonic speeds

Oil-flow visualization and static pressure measurements are employed in an experimental investigation of the flow on the lee surface of flat-top wedge delta wings (normal angle 10 or 20 deg; sweep angle 45,50, 60, or 70 deg) at Mach 0.3-3.0 in the 0.3 x 0.3-m test section of the National Aeronautical Laboratory trisonic wind tunnel. The results are presented in extensive graphs, photographs, and diagrams, and nine distinct flow types are defined and characterized in detail. It is demonstrated that increasing the wing thickness has little effect on the flow type, although the boundaries separating some flow types on the Mach-number/angle-of- attack plane may be shifted