The initial series of wind tunnel tests which were designed to demonstrate the aerodynamic advantages of an advanced technology variable camber wing have been completed. These tests were conducted during twenty-four shifts of occupancy time at the NASA Ames 14-foot transonic wind tunnel between May 21 and June 15, 1973. The configurations tested consisted of the basic F-8, the F-8 with an advanced technology wing, the advanced wing with simple hinged leading and trailing edge flaps and various combinations of smooth, curved variable camber flaps. A summary of the test configurations and test conditions is presented.
Variable Camber Wing
1973
20 pages
Report
No indication
English
Aircraft , Fluid Mechanics , Leading edge flaps , Camber , Transonic characteristics , Wind tunnel models , Model tests , Aerodynamic loading , Moments , Lift , Takeoff , Aircraft landings , Performance(Engineering) , Sweptback wings , Load distribution , Maneuverability , Flutter , Mechanical drawings , Jet fighters , Flaps(Control surfaces) , Aerodynamic characteristics , Supercritical wings , Variable camber wings , F-8 aircraft
NTIS | 1973
NTIS | 1973
Variable wing area and variable camber
Engineering Index Backfile | 1920
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