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Design of an Axisymmetric Afterbody Test Case for CFD Validation
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Author and Affiliation:
Disotell, Kevin J.(NASA Langley Research Center, 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 flow fields must be supported by continuous improvements in fundamental, high-fidelity experiments designed specifically for CFD implementation. In accordance with this effort, the underpinnings of a new test platform referred to herein as the NASA Axisymmetric Afterbody are presented. The devised body-of-revolution is a modular platform consisting of a forebody section and afterbody section, allowing for a range of flow behaviors to be studied on interchangeable afterbody geometries. A body-of-revolution offers advantages in shape definition and fabrication, in avoiding direct contact with wind tunnel sidewalls, and in tail-sting integration to facilitate access to higher Reynolds number tunnels. The current work is focused on validation of smooth-body turbulent flow separation, for which a six-parameter body has been developed. A priori RANS computations are reported for a risk-reduction test configuration in order to demonstrate critical variation among turbulence model results for a given afterbody, ranging from barely-attached to mild separated flow. RANS studies of the effects of forebody nose (with/without) and wind tunnel boundary (slip/no-slip) on the selected afterbody are presented. Representative modeling issues that can be explored with this configuration are the effect of higher Reynolds number on separation behavior, flow physics of the progression from attached to increasingly-separated afterbody flows, and the effect of embedded longitudinal vortices on turbulence structure.
Publication Date: Jun 05, 2017
Document ID:
20170005772
(Acquired Jun 29, 2017)
Subject Category: FLUID MECHANICS AND THERMODYNAMICS
Report/Patent Number: NF1676L-25648
Document Type: Conference Paper
Meeting Information: AIAA Aviation Technology, Integration, and Operations Conference (AVIATION 2017) Conference; 17th; 5-9 Jun. 2017; Denver, CO; United States
Meeting Sponsor: American Inst. of Aeronautics and Astronautics; Reston, VA, United States
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: 17p; In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: No Copyright
NASA Terms: COMPUTATIONAL FLUID DYNAMICS; BOUNDARY LAYER SEPARATION; FLOW DISTRIBUTION; FOREBODIES; AFTERBODIES; SEPARATED FLOW; TURBULENCE MODELS; WIND TUNNELS; REYNOLDS NUMBER; FLUID DYNAMICS
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Last Modified: June 29, 2017
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