Transonic flow past a Whitcomb airfoil with a deflected aileron

Title & Authors
Transonic flow past a Whitcomb airfoil with a deflected aileron
Kuzmin, Alexander;

Abstract
The sensitivity of transonic flow past a Whitcomb airfoil to deflections of an aileron is studied at free-stream Mach numbers from 0.81 to 0.86 and vanishing or negative angles of attack. Solutions of the Reynolds-averaged Navier-Stokes equations are obtained with a finite-volume solver using the $\small{k-{\omega}}$ SST turbulence model. The numerical study demonstrates the existence of narrow bands of the Mach number and aileron deflection angles that admit abrupt changes of the lift coefficient at small perturbations. In addition, computations reveal free-stream conditions in which the lift coefficient is independent of aileron deflections of up to 5 degrees. The anomalous behavior of the lift is explained by interplay of local supersonic regions on the airfoil. Both stationary and impulse changes of the aileron position are considered.
Keywords
Local supersonic regions;Aileron deflection;Instability;Lift coefficient;
Language
English
Cited by
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3.
Sensitivity analysis of transonic flow past a NASA airfoil/wing with spoiler deployments, International Journal of Aeronautical and Space Sciences, 2014, 15, 3, 232
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