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Report
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Annual Report - National Advisory Committee for Aeronautics
Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
NASA Technical Note
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Chordwise and Compressibility Corrections to Slender-wing Theory
Corrections to slender-wing theory are obtained by assuming a spanwise distribution of loading and determining the chordwise variation which satisfies the appropriate integral equation. Such integral equations are set up in terms of the given vertical induced velocity on the center line, or depending on the type of wing plan form, its average value across the span at a given chord station. The chordwise distribution is then obtained by solving these integral equations. Results are shown for flat-plate, rectangular, and triangular wings.
Investigation of the Laminar Aerodynamic Heat-transfer Characteristics of a Hemisphere-cylinder in the Langley 11-inch Hypersonic Tunnel at a Mach Number of 6.8
At the stagnation point, the theory of Sibulkin, using the diameter and conditions behind the normal shock, was in good agreement with the experiment when the velocity graident at the stagnation opint appropriate to the free-stream Mach number was used.
