Theoretical Loading at Supersonic Speeds of Flat Swept-back Wings with Interacting Trailing and Leading Edges
Theoretical Loading at Supersonic Speeds of Flat Swept-back Wings with Interacting Trailing and Leading Edges

Author: Doris Cohen

Publisher:

Published: 1949

Total Pages: 64

ISBN-13:

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By the method of superposition of conical flows, the load distribution is calculated for regions of a long swept-back wing behind the points at which the Mach lines from the trailing-edge apex intersect the leading edge. It is found that a good approximation on the load can be obtained by the application of a fairly simple correction factor to the two-dimensional subsonic distribution. The similarity of two-dimensional flow is used to derive expressions for the loss of lift behind the Mach lines from the tips of the wing.

Investigation of Fretting Corrosion by Microscopic Observation
Investigation of Fretting Corrosion by Microscopic Observation

Author: Douglas Godfrey

Publisher:

Published: 1950

Total Pages: 690

ISBN-13:

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Fretting corrosion was concluded to be caused by the removal of finely divided and apparently virgin material due to inherent forces and that its primary reaction is independent of of vibratory motion or high sliding speeds. Fretting corrosion occurred to clean nonmetals and metals readily and glass microscope slides and steel balls provided an excellent method for visual studies.

Report
Report

Author: United States. National Advisory Committee for Aeronautics

Publisher:

Published: 1953

Total Pages: 40

ISBN-13:

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Analysis of the Effects of Boundary-layer Control on the Power-off Landing Performance Characteristics of a Liaison Type of Airplane
Analysis of the Effects of Boundary-layer Control on the Power-off Landing Performance Characteristics of a Liaison Type of Airplane

Author: Elmer A. Horton

Publisher:

Published: 1950

Total Pages: 678

ISBN-13:

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An investigation was made to determine the effects of boundary-layer control on the landing performance characteristics of a liaison type of airplane having a payload of 1500 pounds and a flight duration of 5 hours. The aspect ratio was varied from 5 to 15, the wing span from 30 to 100 feet, and the brake horsepower from 300 to 1200. The use of boundary-layer control caused reduction in total landing distance (25 to 40 percent), ground-run distance, gliding speed, and stalling speed whereas sinking speed was increased only slightly.