RESEARCH ON HYPERSONIC FLOW OF BLUNT DELTA WINGS. PART II. GAP EFFECTS OF A BLUNT SLAB DELTA WING AT MODERATE SUPERSONIC AND HYPERSONIC SPEEDS.
Final rept. Nov 66-Jan 68,
ARA INC WEST COVINA CALIF
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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 LDmax 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. Reynolds number was kept constant at Rein 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, LD 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
- Fluid Mechanics