The modeling requirements for validating Navier-Stokes computations of a high-lift trapezoidal wing are investigated. This wing has a full-span slat and a full-span flap and has been tested extensively in the NASA Langley 14 x 22-ft Wind Tunnel and the NASA Ames 12-ft Pressure Wind Tunnel. Because of the size of the wing, there are significant facility effects in the data from the 12-ft wind tunnel. Computational models of the test facility of differing fidelity are developed and tested. Results are compared with experimental lift, drag, and surface pressures. In the computations a simplified, inviscid model of the test section performs as well as a high-fidelity, viscous test section model. Computed results generally compare very well with experimental data at all but the highest angles of attack. A comparison of computational results from both free-air and wind-tunnel simulations at the same lift condition indicates that it is necessary to simulate the wind tunnel to perform validation using the 12-ft wind-tunnel experimental data. A subsequent grid-refinement study found that enhanced spanwise resolution increased the accuracy of the computed surface pressures at high angle of attack and resulted in a computed maximum lift that was 5% above the experimental value.
Validation of computed high-lift flows with significant wind-tunnel effects
Validierung von Simulationsmodellen von Tragflügelumströmungen unter Berücksichtigung von Windkanaleffekten
AIAA Journal ; 39 , 10 ; 1884-1892
2001
9 Seiten, 18 Bilder, 30 Quellen
Aufsatz (Zeitschrift)
Englisch
FLUID DYNAMICS - Validation of Computed High-Lift Flows with Significant Wind-Tunnel Effects
Online Contents | 2001
|Wind-tunnel tests of hall high-lift wing
Engineering Index Backfile | 1932
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