A 1/6-scale, semispan model of an AFTI-111 concept equipped with eleven remotely controllable hydraulic actuation systems used to control wing shape and horizontal tail angle was tested in the Propulsion Wind Tunnel (16T) at free-stream Mach numbers of 0.60 and 0.85 and free-stream dynamic pressures of 400 and 500 psf. Angle of attack was varied from 0 to 8 deg. The objectives of this test were to further develop and refine a computer-controlled self-optimizing wing for continual investigation of optimum wing airfoil contours for specific mission profiles. (Author)
Wind Tunnel Test of a Self-Optimizing Flexible Technology Wing
1980
24 pages
Report
Keine Angabe
Englisch
Aircraft , Aerodynamics , Variable sweep wings , Aerodynamic control surfaces , Hydraulic actuators , Airfoils , Optimization , Computer applications , Self operation , Flexible structures , Variables , Wind tunnel tests , Aerodynamic configurations , Subsonic characteristics , Transonic characteristics , Leading edges , Deflection , Angle of attack , Camber , Horizontal stabilizers , Remote control , Jet fighters , Variable camber wings , Deflectable leading edges , Self optimizing wings , SOFT(Self Optimizing Flexible Technology) , F-111 aircraft , Variable geometry aircraft