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

Report Date : JUL 1973

Pagination or Media Count : 29

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)

Descriptors :   *SWEPTBACK WINGS), (*CAMBER, AERODYNAMIC CONFIGURATIONS, AERODYNAMIC LOADING, COSTS, PERFORMANCE(ENGINEERING), TRANSONIC CHARACTERISTICS, FLUTTER, JET FIGHTERS, FLAPS(CONTROL SURFACES), MACH NUMBER, ANGLE OF ATTACK, YAW, AILERONS, REYNOLDS NUMBER, DEFLECTION, AERODYNAMIC CHARACTERISTICS, SUPERSONIC CHARACTERISTICS.

Subject Categories : Attack and Fighter Aircraft
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE