Wind Tunnel Measurements of the Magnus Induced Surface Pressures on a Spinning Artillery Projectile Model in the Transonic Speed Regime

摘要

The aerodynamic surface pressures on a spinning projectile were experimentally obtained during transonic wind tunnel tests employing a novel model design and instrumentation arrangement. A series of remotely controlled pressure taps located in the non-spinning inner portion of the wind tunnel model detected the surface pressures through vent holes in the spinning outer portion. Data were obtained at spin rates of 0 and 82 Hz for angles of attack of 0, 4, and 10 deg. Testing was conducted at a Mach number of 0.94 and Reynolds number of 4 million per foot. The results illustrate the large circumferential pressure variation over the boattail region as well as the nonlinear effect of the angle of attack. The integrated pressure data indicate not only the total Magnus force and moment coefficients for the model, but also the individual contributions of the various body components.