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Development of an Axisymmetric Afterbody Test Case for Turbulent Flow Separation ValidationAs identified in the CFD Vision 2030 Study commissioned by NASA, validation of advanced RANS models and scale-resolving methods for computing turbulent flows must be supported by improvements in high-quality experiments designed specifically for CFD implementation. A new test platform referred to as the Axisymmetric Afterbody allows for a range of flow behaviors to be studied on interchangeable afterbodies while facilitating access to higher Reynolds number facilities. A priori RANS computations are reported for a risk-reduction configuration to demonstrate critical variation among turbulence model results for a given afterbody, ranging from barely-attached to mild separated flow. The effects of body nose geometry and tunnel-wall boundary condition on the computed afterbody flow are explored to inform the design of an experimental test program.
Document ID
20170011474
Acquisition Source
Langley Research Center
Document Type
Technical Memorandum (TM)
Authors
Disotell, Kevin J. (Universities Space Research Association Hampton, VA, United States)
Rumsey, Christopher L. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
December 1, 2017
Publication Date
November 1, 2017
Subject Category
Aerodynamics
Fluid Mechanics And Thermodynamics
Report/Patent Number
NASA/TM-2017-219680
NF1676L-28486
L-20890
Funding Number(s)
WBS: WBS 109492.02.07.01.01
Distribution Limits
Public
Copyright
Public Use Permitted.

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