Large increases in lift-curve slope at low angles of attack at high supersonic Mach numbers can be obtained by the use of wedge-shape airfoil sections. The use of such sections on the tail surfaces operating at low angles of attack on airplanes or missiles traveling at these speeds can greatly decrease the stabilizing-surface area required. Moderate increases in section effectiveness (lift-curve slope) over that for more conventional tail sections can be obtained with little or no increase in total drag because of the decreased surface area required. Larger increases can be obtained;however, they will be accompanied by increases in stabilizing-surface drag.
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