Iterative Calculation of Flow Past a Thick Cambered Wing Near the Ground,
Abstract
A method to compute the steady low-speed inviscid flow past a wing in free air, is extended to take account of ground effect. The basic method represents the perturbation due to the wing by iteratively computed distributions of sources and doublets on the wing chordal surface; at each iteration the ground effect is represented by the images in the ground plane of these distributions, the strengths of which are calculated from the computed errors in the boundary conditions on upper and lower surfaces. For a given angle of incidence (and Mach number), several heights above the ground in succession can be treated, with some economy in computing time. Results are presented for a two-dimensional section (RAE 100) and for two variants of a wing of airbus type. Comparisons with another method for the RAE 100 section suggest that the present method generally needs at least three iterations, and that for very accurate results at low ground heights further work on the program is needed.
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1976
- Accession Number
- ADA041583
Entities
People
- C. C. L. Sells