Standard Dynamics Model Experiments with the DFVLR/AVA Transonic Derivative Balance,
INSTITUT FUER AEROELASTIK GOETTINGEN (GERMANY F R)
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A slender high-load forced-oscillation measuring system for dynamic derivatives of aircraft and missile models in a transonic wind tunnel is presented together with typical test results of the significant aerodynamic coefficients and stability derivatives of the Standard Dynamics Model, a simplified fighter aircraft model with a wing span of 0.345 m. The measurements in the rotational modes pitch, yaw and roll encompass Mach numbers from 0.6 to 1.2, angles of attack from 0 to 30 degrees and excitation frequencies from 2 to 20 Hz at a constant Reynolds number of 7.8 Miom. Most of the stiffness and damping derivatives gathered show substantial nonlinear dependence on Mach number and angle of attack, where-as the influence of reduced frequency is less prominent. The results are closely related to published measurements on Standard Dynamic models performed in other NATO countries.