A general question posed in aerodynamics is 'what is the maximum lift which can be obtained from an airfoil and what is the shape of that airfoil?' Computational Fluid Dynamics (CFD) techniques are used to answer this question and to improve airfoil design. A nonlinear method is first used to design velocity distribution that will optimize the lift generated. This velocity distribution is then modified to enable the design of a practical airfoil shape. An airfoil is then designed using an inverse airfoil technique. Finally, a panel method along with a boundary layer solver are used to calculate pressure distributions, lift and drag of the optimized airfoils. It is shown that the optimized airfoils developed by these methods will offer subtantial improvements in performance over similar NACA airfoils.
On the design for maximum lift airfoils
Konstruktion von Tragflügeln mit maximalem Auftrieb
1991
12 Seiten, 17 Bilder, 1 Tabelle, 22 Quellen
Conference paper
English
Optimization of airfoils for maximum lift
AIAA | 1970
|Optimization of airfoils for maximum lift
AIAA | 1969
|Maximum lift-to-drag ratio airfoils at moderate supersonic speeds
Engineering Index Backfile | 1969
|