Dynamic Force Measurements and Boundary-Layer Transition Mapping on a Spinning 9-Deg Cone with and without Mass Addition at Mach Numbers 5 and 8
Final rept. Nov 1977-Jan 1978
ARO INC ARNOLD AFS TN
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A wind tunnel test program was conducted to determine the effect of spin on the aerodynamic forces and moments and the shape and movement of the boundary-layer transition zone on 9-deg half-angle cone configurations. The effects of nose geometry, mass addition, angle of attack, Mach number, and Reynolds number were investigated at various spin rates. Results were obtained using a spin mechanism 1-DOF developed for this test and a three degree-of- freedom 3-DOF mechanism. The test was conducted at Mach numbers 5 and 8 at free-stream Reynolds numbers, based on model length, ranging from 1.6 to 24 million and angles of attack ranging from -6 to 6 deg. The dynamic heat-transfer rate results were corrected for gage response characteristics with the use of the digital Fourier Analysis technique. The dynamic results were generally in good agreement with the steady-state results. The data obtained from the spin tests indicated there were no effects of spin on the transition zone nor were there any induced lateral forces or moments produced at the test conditions of this test.
- Fluid Mechanics