Some examples of the applications of the transonic and supersonic area rules to the prediction of wave drag
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Nelson, Robert L↗
Engineering topics
Welsh, Clement J
Publications and source records attributed to Welsh, Clement J.
Results of a Flight Investigation to Determine the Zero-lift Drag Characteristics of a 60 Degree Delta Wing with NACA 65-006 Airfoil Section and Various Double-wedge Sections at Mach Numbers from 0.7 to 1.6
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Welsh, Clement J↗
Free-flight Investigation to Obtain Drag-at-lift and Stability Data for a 60 Degree Delta-wing--body Configuration over a Mach Number Range of 1.3 to 1.6
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Welsh, Clement J↗
Effects of Some Leading-edge Modifications, Section and Plan-form Variations, and Vertical Position on Low-lift Wing Drag at Transonic and Supersonic Speeds
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Welsh, Clement J↗
Results of Flight Tests to Determine the Drag of Finite-length Cylinders at High Reynolds Numbers for a Mach Number Range of 0.5 to 1.3
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Welsh, Clement J↗
Results of Flight Tests to Determine Drag of Parabolic and Cone-cylinder Bodies of Very Large Fineness Ratios at Supersonic Speeds
Results of a free-flight investigation at supersonic speeds to determine zero-lift drag of a series of bodies of revolution are presented. Configurations tested included two parabolic bodies with fineness ratios of 17.78 and 24.5 and two 8 degree cone-cylinder bodies with fineness ratios of 17.2 and 21.2. Results of previous tests of similar parabolic bodies but with lower fineness ratios are included in this paper for comparison. All bodies for which data are presented in this paper had a base-to-maximum-diameter ratio of 0.437. Calculated drag coefficients are shown for all bodies for which data are presented. (author)
Welsh, Clement J↗
Flight Investigation at Mach Numbers from 0.8 to 1.5 of the Drag of a Canopy Located at Two Positions on a Parabolic Body of Revolution
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Welsh, Clement J↗
Results of flight tests to determine the zero-lift drag characteristics of a 60 degree delta wing with NACA 65-006 airfoil section and various double-wedge sections at Mach numbers from 0.7 to 1.6
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Welsh, Clement J↗
Effect of Wing-tank Location on the Drag and Trim of a Swept-wing Model as Measured in Flight at Transonic Speeds
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Welsh, Clement J↗