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Record Details

Record 19 of 624
Turbulence Model Comparisons and Reynolds Number Effects Over a High-Speed Aircraft at Transonic Speeds
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Author and Affiliation:
Rivers, Melissa B.(NASA Langley Research Center, Hampton, VA United States)
Wahls, Richard A.(NASA Langley Research Center, Hampton, VA United States)
Abstract: This paper gives the results of a grid study, a turbulence model study, and a Reynolds number effect study for transonic flows over a high-speed aircraft using the thin-layer, upwind, Navier-Stokes CFL3D code. The four turbulence models evaluated are the algebraic Baldwin-Lomax model with the Degani-Schiff modifications, the one-equation Baldwin-Barth model, the one-equation Spalart-Allmaras model, and Menter's two-equation Shear-Stress-Transport (SST) model. The flow conditions, which correspond to tests performed in the NASA Langley National Transonic Facility (NTF), are a Mach number of 0.90 and a Reynolds number of 30 million based on chord for a range of angle-of-attacks (1 degree to 10 degrees). For the Reynolds number effect study, Reynolds numbers of 10 and 80 million based on chord were also evaluated. Computed forces and surface pressures compare reasonably well with the experimental data for all four of the turbulence models. The Baldwin-Lomax model with the Degani-Schiff modifications and the one-equation Baldwin-Barth model show the best agreement with experiment overall. The Reynolds number effects are evaluated using the Baldwin-Lomax with the Degani-Schiff modifications and the Baldwin-Barth turbulence models. Five angles-of-attack were evaluated for the Reynolds number effect study at three different Reynolds numbers. More work is needed to determine the ability of CFL3D to accurately predict Reynolds number effects.
Publication Date: Dec 01, 1999
Document ID:
20000044873
(Acquired Jun 02, 2000)
Subject Category: AERODYNAMICS
Document Type: Conference Paper
Publication Information: First NASA/Industry High-Speed Research Configuration Aerodynamics Workshop; Part 3; 1185-1214; (NASA/CP-1999-209690/PT3); (SEE 20000044865)
Financial Sponsor: NASA Langley Research Center; Hampton, VA United States
Organization Source: NASA Langley Research Center; Hampton, VA United States
Description: 30p; In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: No Copyright
NASA Terms: BALDWIN-LOMAX TURBULENCE MODEL; TURBULENT FLOW; REYNOLDS NUMBER; TRANSONIC FLOW; TRANSONIC WIND TUNNELS; COMPUTATIONAL FLUID DYNAMICS; GRID GENERATION (MATHEMATICS); UPWIND SCHEMES (MATHEMATICS); NAVIER-STOKES EQUATION; MATHEMATICAL MODELS; WIND TUNNEL MODELS; AIRSPEED; ANGLE OF ATTACK; MACH NUMBER; SHEAR STRESS; STRESS ANALYSIS; PRESSURE DISTRIBUTION
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