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Development of an Axisymmetric Afterbody Test Case for Turbulent Flow Separation Validation
NTRS Full-Text: Click to View  [PDF Size: 2.1 MB]
Author and Affiliation:
Disotell, Kevin J.(Universities Space Research Association, Hampton, VA, United States)
Rumsey, Christopher L.(NASA Langley Research Center, Hampton, VA, United States)
Abstract: As 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.
Publication Date: Nov 01, 2017
Document ID:
20170011474
(Acquired Dec 11, 2017)
Subject Category: AERODYNAMICS; FLUID MECHANICS AND THERMODYNAMICS
Report/Patent Number: NASA/TM-2017-219680, L-20890, NF1676L-28486
Document Type: Technical Report
Contract/Grant/Task Num: WBS 109492.02.07.01.01
Financial Sponsor: NASA Langley Research Center; Hampton, VA, United States
Organization Source: NASA Langley Research Center; Hampton, VA, United States
Description: 34p; In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: Copyright; Public use permitted
NASA Terms: COMPUTATIONAL FLUID DYNAMICS; AFTERBODIES; TURBULENCE MODELS; BOUNDARY LAYER SEPARATION; SEPARATED FLOW; BOUNDARY CONDITIONS; TURBULENT FLOW; REYNOLDS NUMBER; WALLS
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