Abstract:
An analysis is presented of measurements made at RAE in 1957-1959 on a series of delta wings. Lift and drag have been measured by strain-gauge balance at Mach numbers between 1.4 and 2.8. On some of the wings surface pressure distributions have also been measured. This Report deals mainly with the zero-lift wave drag, but also gives information on skin friction drag and lift-dependent drag. The wave drag has been obtained by integrating the pressure distribution. Values of the wave drag have also been derived from the measured total drag by subtracting estimated values for the skin-friction drag and for the effect of the sting support. The experimental values are compared with one another and with the theoretical estimates derived by supersonic area rule. The different experimental values are shown to be selfconsistent and to lie up to 30% below the theoretical estimates.
