It was found that the maximum lift to drag ratio of a flat delta wing at moderate supersonic and hypersonic speeds can be increased appreciably by letting a small amount of air pass through narrow gaps located at proper places on the wing. The increase in (L/D)max obtained from such a wing experiment varies from 5% to 17% at different speeds. Six gap configurations were tested at four different free stream Mach numbers, M = 4, 4.5, 5 and 8. Reynold's number was kept constant at Re/in = 300,000 and 700,000. Both the lift and drag of the wing were reduced due to the presence of gaps. Since the decrease in drag is greater than that of lift, L/D is thus increased. The reduction in lift is due to the loss of momentum and the increase of pressure in the induced separation region on the leeward side of the wing; the reduction in drag is due to the decrease in skin-friction caused by gap effects. (Author)
Research on Hypersonic Flow of Blunt delta Wings. Part II. Gap Effects of a Blunt Slab delta Wing at Moderate Supersonic and Hypersonic Speeds
1968
86 pages
Report
No indication
English
Aircraft , Fluid Mechanics , Aerodynamics , Delta wings , Hypersonic characteristics , Blunt bodies , Supersonic characteristics , Aerodynamic slots , Lift , Drag , Skin friction , Swept-back wings , Angle of attack , Reynolds number , Boundary layer , Flow separation , Injection , Reduction , Lift drag ratio , Gap effects
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