Abstract : Wind tunnel tests were conducted to determine the damping-in-pitch derivatives of 120- and 140-deg blunted, conical models with and without base fairings. Measurements were made with a forced-oscillation dynamic balance as the model oscillated + or - 1.8 deg at angles of attack ranging from -5.9 to 39. 4 deg. Data were obtained at nominal Mach numbers of 0.6 to 3 and at free-stream Reynolds numbers, based on maximum model diameters, ranging from 370,000 to 1, 620,000. In general for all configurations the damping derivatives at zero angle of attack were a strong nonlinear function of Mach number and showed the models to be dynamically unstable at Mach numbers from about 1.1 to 2.1. However, as angle of attack increased, model stability increased and the derivatives were found to vary in a less nonlinear manner with Mach number. At free stream Mach numbers of 1.9, 2.3, and 2.65 Reynolds number effects were investigated and it was noted that the damping-in-pitch derivatives were influenced strongly by Reynolds number. Addition of different base fairings produced no large changes in the damping derivatives.
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