PRESSURE DISTRIBUTIONS OVER FRONTAL (NOSE) SURFACES OF BODIES OF REVOLUTION IN TRANSONIC FLOW AT ANGLES OF ATTACK alpha equals 0 to 10 degree .

Measurements of pressure distribution in meridional planes of nose surfaces of various curvatures, ranging from a hemisphere to a flat surface, in transonic flow (M equals 0. 7 to 1. 25) at angles of attack alpha equals 0. 5 and 10 degree are presented. Analysis of data suggests an empirical method for determining the pressure coefficient for such nose surfaces. It is shown that the experimental data at alpha equals 0 are in agreement with available theoretical calculations.