Aerothermodynamic environment predictions in support of the Aeroassist Flight ExperimentA computational fluid dynamic (CFD) simulation has been made of the flow past an Aeroassist Flight Experiment (AFE) aerobrake model with a payload and sting. The simulation involves solving the complete Navier-Stokes equations in three dimensions. Comparisons with data taken in a Mach 10 wind tunnel test are made and agreement is shown to be very good. Points of comparison include the aerobrake surface pressure and heat transfer rate, the sting surface streamlines, and the sting heat transfer rate. The dependence of the solution on the grid is also explored. Finally, predictions are made for conditions which correspond to a hypersonic shock tunnel force and moment test to be carried out later this year.
Document ID
19910062575
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Fay, John F. (Sverdrup Technology, Inc. Huntsville, AL, United States)
Kumar, Ganesh N. (Sverdrup Technology, Inc. Huntsville, AL, United States)
Seaford, C. M. (NASA Marshall Space Flight Center Huntsville, AL, United States)