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Computational flow predictions for hypersonic drag devicesThe effectiveness of two types of hypersonic decelerators is 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 extend 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. Heat transfer rates to the SRM and the decelerators are predicted to estimate the amount of thermal protection required.
Document ID
19950005554
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Tokarcik, Susan A. (Eloret Corp. Palo Alto, CA, United States)
Venkatapathy, Ethiraj (Eloret Corp. Palo Alto, CA, United States)
Date Acquired
September 6, 2013
Publication Date
January 1, 1993
Publication Information
Publication: NASA. Ames Research Center, Technical Paper Contest for Women 1992. Space Challenges: Earth and Beyond
Subject Category
Aerodynamics
Accession Number
95N11967
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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