COMPARISON OF SHOCK-EXPANSION THEORY WITH EXPERIMENT FOR THE LIFT, DRAG, AND PITCHING-MOMENT CHARACTERISTICS OF TWO WING-BODY COMBINATIONS AT M = 5.0

摘要

Lift, drag, and pitching-moment coefficients for two wing-body combinations were determined from tests at a Mach number of 5.0.and angles of attack up to 9°. The test models consisted of small thin wings mounted on a body composed of a fineness-ratio-3 ogival nose and a fineness-ratio-2 cylindrical afterbody. The wings were symmetrically mounted on the cylin¬drical portion of the body and had triangular and trapezoidal plan forms.nThe results of these tests are compared with results obtained by a relatively simple application of the generalized shock-expansion method in combination with the T' method of evaluating the, skin-friction drag coefficients. Good agreement between theory and experiment is obtained for the total drag coefficients over the test angle-of-attack range. Theory and experiment are also found to be in good agreement for the lift and pitching-moment coefficients at the lower angles of attack. At the higher angles of attack, the theoretically determined coefficients are somewhat higher than those obtained experimentally.