AN EFFICIENT AND ACCURATE APPROACH FOR ANALYSIS AND DESIGN OF HIGH LIFT CONFIGURATIONS

A calculation method for the aerodynamic prediction of multi-element airfoils and wings based on an interactive boundary-layer approach using an improved Cebeci-Smith eddy viscosity formulation is described. Results are first presented for single airfoils at low and moderate Reynolds numbers in order to demonstrate the need to calculate transition for accurate drag polar prediction and the ability of the improved Cebeci-Smith turbulence model to predict flows with extensive separation, and therefore to predict maximum lift coefficient. Results, in terms of pressure distributions and lift, drag and moment coefficients, are presented for a series of multi-element airfoils with flaps and slats. Results are then presented for single- and multi-element wing configurations. The importance of the compressibility effects and the turbulence model on stall, and, again, the need to calculate the onset of transition, are demonstrated.