Wind-tunnel wall interference effects were estimated using numerical solutions capable of computing the flow field over complex three-dimensional bodies. This approach was then tested by applying it to two typical wind tunnel experiments involving a high-lift wing and a fighter airplane model. In both cases, the static pressure signature along the test section walls was measured and computed for additional validation. The wind-tunnel wall correction method described here, which inherently includes effects of lift and blockage, provides more details than previous semiempirical methods.
Application of panel methods to wind-tunnel wall interference corrections
01.01.1990
Aufsatz (Konferenz)
Keine Angabe
Englisch
NTRS | 1948
|Tema Archiv | 1996
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