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An Application of CFD to Guide Forced Boundary-Layer Transition for Low-Speed Tests of a Hybrid Wing-Body ConfigurationA hybrid transition trip-dot sizing and placement test technique was developed in support of recent experimental research on a hybrid wing-body configuration under study for the NASA Environmentally Responsible Aviation project. The approach combines traditional methods with Computational Fluid Dynamics. The application had three-dimensional boundary layers that were simulated with either fully turbulent or transitional flow models using established Reynolds-Averaged Navier-Stokes methods. Trip strip effectiveness was verified experimentally using infrared thermography during a low-speed wind tunnel test. Although the work was performed on one specific configuration, the process was based on fundamental flow physics and could be applicable to other configurations.
Document ID
20160010156
Document Type
Conference Paper
Authors
Luckring, James M. (NASA Langley Research Center Hampton, VA, United States)
Deere, Karen A. (NASA Langley Research Center Hampton, VA, United States)
Childs, Robert E. (Science and Technology Corp. Moffett Field, CA, United States)
Stremel, Paul M. (Science and Technology Corp. Moffett Field, CA, United States)
Long, Kurtis R. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 9, 2016
Publication Date
June 13, 2016
Subject Category
Aerodynamics
Fluid Mechanics and Thermodynamics
Report/Patent Number
NF1676L-22883
Meeting Information
AIAA Applied Aerodynamics Conference(Washington, DC)
Funding Number(s)
WBS: WBS 338881.02.27.07.01.01
Distribution Limits
Public
Copyright
Public Use Permitted.

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