Abstract
Dangerous asymmetrical thrust components which act on the nozzle wall as side loads can occur during the low-altitude operating phase of a launcher when the flow is separated within the extension. To try to get a better understanding of this phenomenon, a numerical study of the unsteady side-loads occurring in a thrust-optimized contour nozzle is presented. Depending on the pressure ratio either a free shock or a restricted shock separation is observed with a significant hysteresis between these two flow regimes. The present effort is focused on a pressure ratio for which both shock patterns are observed at stationary conditions (hysteresis regime). The main features of the flowfield as well as the resulting side loads are described for both shock configurations. Statistical and spectral properties of side loads are analyzed and compared with the available experimental data. Finally, a semi-empirical method based on random pressure pulsations is suggested to assess the spectral distribution of side loads occurring in the free shock separation regime
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