MEASURED PRESSURE DISTRIBUTIONS AND SHOCK SHAPES ON A SIMPLE DELTA WING.

This note presents the results of an experimental investigation of the flow over a simple delta wing designed for a Mach number of 3. 5. Complete pressure distributions were measured for incidences of 0 degree , 10 degree and 20 degree at Mach numbers of 2. 5 and 3. 5. A number of schlieren photographs of the shock system around the wing were obtained at the same conditions and surface streamline patterns were studied at M equals 3. 5. The measurements were made to support numerical calculations which use this wing as a test case.