Sting Interference Effects on the Static Dynamic, and Base Pressure Measurements of the Standard Dynamics Model Aircraft at Mach Numbers 0.3 through 1.3

Wind tunnel tests were conducted in the Arnold Engineering development Center (AEDC) Propulsion Wind Tunnel Facility (PWT) to provide sting-support interference information for planning and directing wind tunnel tests at subsonic and transonic Mach numbers. Sting length and diameter effects on static and dynamic stability derivatives, static pitching moments, and base pressure of the Standard Dynamics Model (SDM) were investigated at Mach numbers from 0.3 to 1.3. Dynamic stability derivatives were obtained at a nominal frequency of 5.2 Hz, at amplitudes of 1.0, 1.5, and 2.0 deg. Pitch and yaw data were both obtained as a function of angle of attack. Previously unpublished static force and moment data for the SDM are also presented. The results showed that interference related to sting length was most pronounced at Mach number 0. 95 for all measurements; the results also showed significant effects at Mach numbers 1.1 and 1.3 for yaw damping. Substantial sting diameter effects were observed at Mach number 0.3 for pitch damping and at Mach number 1.3 for yaw damping. Both sting length and diameter effects were found in base-pressure measurements at most Mach numbers. Prepared in cooperation with ARO, Inc., Tullahoma, TN.