NASA NTRS · 19950062151
Numerical study of multi-element airfoil aerodynamics
Abstract
Unsteady flowfields around oscillating Boeing VR7 airfoil with and without a leading-edge slat were numerically investigated by a novel zonal method using a conformal mapping technique. Numerical aero-dynamic hysteresis loops show that the leading-edge slat prevents the airfoil dynamic stall at reduced frequency of 0.15, Reynolds number of 1 million, and the oscillation range of 5 deg to 25 deg.
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Wang, Clin M., Tung, Chee. 1992-01-01. Numerical study of multi-element airfoil aerodynamics. https://ntrs.nasa.gov/citations/19950062151
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