Accession Number:

AD0912129

Title:

Variable Camber Wing.

Descriptive Note:

Progress rept. no. 3 for period ending 15 Jul 73.

Corporate Author:

BOEING AEROSPACE CO SEATTLE WA

Personal Author(s):

Report Date:

1973-07-01

Pagination or Media Count:

29.0

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

Subject Categories:

  • Attack and Fighter Aircraft
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE