Accession Number : ADP004054

Title :   Recent Advances in Computational Methods to Solve the High-Lift Multi-Component Airfoil Problem,

Corporate Author : NATIONAL AEROSPACE LAB AMSTERDAM (NETHERLANDS)

Personal Author(s) : Oskam,B. ; Laan,D. J. ; Volkers,D. F.

Report Date : AUG 1984

Pagination or Media Count : 31

Abstract : Current research in the area of high-lift aerodynamics is directed towards development of a computational design capability for high-lift systems consisting of flaps and slats. The development of mathematical models to analyze viscous flow over high-lift multi-component airfoil configurations is the first phase in such a research program. This paper describes recent advances made in solving this high-lift multicomponent airfoil problem. Two particular aspects of the problem are addressed. The first aspect concerns the calculation of viscous wakes subjected to large adverse pressure gradients. This 'off-the-surface' pressure recovery is a flow feature unique to multi-component airfoils, and is not present in the single-component airfoil problem. The second aspect dealt with concerns the locally supersonic flow over the slat of a high-lift configuration, with a free stream Mach number of around 0.2. In this 'low speed' regime the highest local velocities are found to reach Mach numbers of around 1.6 indicating that in the final analysis of viscous flow over high-lift multi-component airfoil configurations it is imperative to include the nonlinear compressible flow effects.

Descriptors :   *Aerodynamic control surfaces, Mathematical models, High lift, Airfoils, Parts, Viscous flow, Supersonic flow, Subsonic characteristics, Wake, Pressure gradients, Adverse conditions, Leading edge flaps, Compressible flow, Nonlinear analysis, Pressure, Recovery, Netherlands

Distribution Statement : APPROVED FOR PUBLIC RELEASE