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)
Variable Camber Wing
1973
29 pages
Report
No indication
English
Aircraft , Fluid Mechanics , Camber , Sweptback wings , 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 , F-8 aircraft , Supercritical wings , Variable camber wings , A-7 aircraft , F-4 aircraft , S-3 aircraft
NTIS | 1973
NTIS | 1973
Variable wing area and variable camber
Engineering Index Backfile | 1920
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