Experimental study of aerodynamic characteristics of a reentry vehicle on a setup with free oscillations at supersonic velocities
N.P. Adamov1, A.M. Kharitonov1, E.A. Chasovnikov1, A.A. Dyad’kin2, A.N. Krylov2, and E.N. Aleksandrov2
1 Khristianovich Institute of Theoretical and Applied Mechanics SB RAS, Novosibirsk, Russia
2 Korolev Rocket and Space Corporation “Energia”, Korolev, Moscow region, Russia
E-mail: chas@itam.nsc.ru
Keywords: reentry vehicle, free oscillations, pitch damping coefficient, aerodynamic characteristics
Pages: 791–800
Abstract
A setup with free oscillations containing a transverse sting for holding the test model and possible test regimes are described. The method of testing and data processing is presented. Aerodynamic characteristics of the pitching moment of the model in a wide range of Mach numbers are obtained. Comparisons of quasi-steady data with numerical predictions and of damping derivatives with those obtained previously in tests of the model mounted on the base sting and with calculated results are performed. The model is found to be statically and dynamically stable except for regimes with М = 1.75 and 2.25, where nondecaying oscillations are excited.
DOI: 10.1134/S0869864316060019
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