Variable Camber Wing.
Abstract
The variable camber wind tunnel tests at NASA-Ames were completed on July 6. These tests were conducted on both the basic F-8 and the advanced technology wing configurations at Mach numbers ranging from .2 to 2.0. First order estimates of the cost and performance implications when the F-4 is substituted for the F-8 as a variable camber wing demonstrator indicate that the cost of the F-4 modification would be 43% higher than for the F-8. Estimates of the performance improvements that could be achieved through the application of variable camber to the F-4, A-7, and S-3 have been accomplished. The wing flutter analysis shows that adequate flutter margins exist for the strength designed wing. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1973
- Accession Number
- AD0912129
Entities
Organizations
- Boeing