Computational flow predictions for hypersonic drag devices

Susan Tokarcik, Ethiraj Venketapathy, Graham Candler, Grant Palmer

Research output: Chapter in Book/Report/Conference proceedingConference contribution

1 Scopus citations

Abstract

The effectiveness of two types of hypersonic decelerators are computationally examined: mechanically deployable flares and inflatable ballutes. Computational fluid dynamics (CFD) is used to predict the flowfield around a solid rocket motor (SRM) with a deployed decelerator. The computations are performed with an ideal gas solver using an effective specific heat ratio of 1.15. The results from the ideal gas solver are compared to computational results from a thermochemical nonequilibrium solver. The surface pressure coefficient, the drag, and the extent of the compression corner separation zone predicted by the ideal gas solver compare well with those predicted by the nonequilibrium solver. The ideal gas solver is computationally inexpensive and is shown to be well suited for preliminary design studies. The computed solutions are used to determine the size and shape of the decelerator that are required to achieve a drag coefficient of 5 in order to assure that the SRM will splash down in the Pacific Ocean. Heat transfer rates to the SRM and the decelerators are predicted to estimate the amount of thermal protection required.

Original languageEnglish (US)
Title of host publication9th Applied Aerodynamics Conference, 1991
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
StatePublished - Jan 1 1991
Event9th Applied Aerodynamics Conference, 1991 - Baltimore, United States
Duration: Sep 23 1991Sep 25 1991

Other

Other9th Applied Aerodynamics Conference, 1991
CountryUnited States
CityBaltimore
Period9/23/919/25/91

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