Frederick C. Grant

Morton Cooper

A linearized theoretical analysis has been made to determine minimum-wave-drag airfoil sections for arrow wings having the same airfoil sections at all spanwise stations. The drag of the wings was minimized subject to the condition of either a given thickness ratio at a specified chordwise location or a given volume. Numerical computations of the airfoil shape and wing wave drag were performed for a delta wing and for an arrow wing having a ratio of the tangent of the trailing-edge sweep angle to the tangent of the leading-edge sweep angle of 0.4. The range of the ratio of the tangent of the leading-edge sweep angle to the tangent of the Mach line sweep angle extended from 0 (two-dimensional) to 2.5.

Minimum-wave-drag Airfoil Sections for Arrow Wings

The results show a 6-percent drag reduction due to twisting a flat delta wing with sonic leading edges and a steady decrease in the gains as sweepback increases.

The Use of Pure Twist for Drag Reduction on Arrow Wings with Subsonic Leading Edges

Importance of the Variation of Drag with Lift in Minimization of Satellite Entry Acceleration

United States. National Advisory Committee for Aeronautics

Benjamin Milwitzky

Keith C. Harder

Milton Van Dyke

Vasily D. Prian

Curt A. Holzhauer

Francis E. Cook

Harry Press

Herbert C. Nelson

James J. Kramer

Maurice Tucker

Richard T. Whitcomb

Conrad Rennemann

Herbert J. Cunningham

May T. Meadows

Richard S. Bray

Chung-Hua Wu

Ivan Hadlock

Wind-tunnel and Flight Investigations of the Use of Leading-edge Area Suction for the Purpose of Increasing the Maximum Lift Coefficient of a 35 ̊swept-wing Airplane

Frederick C. Grant

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