Tables for the Computation of Wave Drag of Arrow Wings of Arbitrary Airfoil Section
Description:
Tables and computing instructions for the rapid evaluation of the wave drag of delta wings and of arrow wings having a ration of the tangent of the trailing-edge sweep angle to the tangent of the leading-edge sweep angle in the range from -1.0 to 0.8. The tables cover a range of both subsonic and supersonic leading edges.
Date:
June 1954
Creator:
Grant, Frederick C. & Cooper, Morton
Item Type:
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