A procedure for the evaluation of wall interference corrections for three-dimensional models is presented. In addition to Mach number and angle-of-attack corrections, the procedure provides an estimate of the accuracy of the corrections. Lift, pitching moment, and pressure measurements near the tunnel walls are required by the correction method. The method is demonstrated by application to an isolated wing model and to a wing-body-tail configuration.
Wind tunnel wall interference corrections for aircraft models in the transonic regime
Journal of Aircraft ; 21
1984-01-01
Sonstige
Keine Angabe
Englisch
Emerging Technology for Transonic Wind-Tunnel-Wall Interference Assessment and Corrections
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