RESEARCH ON HYPERSONIC FLOW OF BLUNT DELTA WINGS. PART III. 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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An experimental investigation of the effect of air ejecting from the windward side to the leeward side through gaps located on a delta wing on the aerodynamic performance was made at hypersonic speeds, M 6 and 10, and at three Reynolds numbers, Reft 1,500,000, 1,600,000 and 3,800,000. The tested data and the oil flow photographs indicate that the gap effect has a negligible influence on the lift and drag of the wing at the tested Mach numbers and Reynolds numbers. The model used in these tests was the same as that used for the previous experiment Part II wherein the gap width varied from 0.015 inch to 0.045 inch. In addition to the measurement of lift and drag, velocity profiles, surface pressures and base pressures were also measured in the present experiment. Author
- Fluid Mechanics