Pressure Distributions on Some Delta Wings at M=4.

Complete pressure distributions are presented for a series of delta wings tested through an incidence range at a Mach number of 4. The results have been integrated to obtain lift and drag coefficients and the values found are in good agreement with the trend from measurements on similar wings at lower Mach numbers. Some of the models were designed to test a possible method of engineairframe integration. The results show that it is possible to add volume to the rear of the wing without increasing the drag of the forebody, thus confirming the proposed method of integration. Author