Abstract
An Euler solver based on the finite-volume Runge-Kutta time-stepping scheme has been developed to predict the flow around airfoils and wings in ground effect. The technique is applied to a Clark Y-airfoil and a low-aspect-ratio wing (Clark Y-airfoil section) in subsonic flow. Results are compared with experimental data and PANAIR (panel method code) calculations.
Original language | English |
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Pages (from-to) | 10-15 |
Number of pages | 6 |
Journal | AIAA Paper |
DOIs | |
State | Published - 1986 |