Investigation of a Variable Camber Wing Design.
Abstract
The principal objective of this NASC sponsored investigation involved definition of the buffet free ttransonic maneuvering benefits derivable from an innovative skewed hingeline variable camber wing design concept. These benefits have been established from comparisons of the predicted performance obtainable with this camber concept with those of conventional uncambered and fixed camber wing designs in a common aircraft application. The aircraft configuration considered in these performance comparisons was selected as representative of an advanced lightweight fighter aircraft. Wing aerodynamic characteristics for the differing aircraft configurations were established from analysis of experimental data available from prior test programs. Analytical methods were utilized to aid in the analysis required to evaluate the influence of Reynolds number and test installation interference effects upon the experimental results. For the aircraft configuration of this study program, it was found that substantial improvements to buffet-free performance could be attained from implementation of this camber concept. For subsonic flight conditions the maximum buffet free performance was attained with a camber scheduling which also yielded minimum drag. At transonic conditions, however, greatest improvements in buffet free performance was achieved only with wing camber configurations producting aircraft drag levels above the minimum.
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1977
- Accession Number
- ADA045951
Entities
People
- L. D. Robinson
- T. D. Beatty
- W. B. Brooks
Organizations
- Vought