The Effect of Simulated Icing on Propeller Performance

The Effect of Simulated Icing on Propeller Performance PDF

Author: Blake W. Corson

Publisher:

Published: 1946

Total Pages: 42

ISBN-13:

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Tests of a 10-foot-diameter three-blade Curtiss 89301-15 propeller with Clark Y blade sections have been conducted in the Langley 16-foot high-speed tunnel in order to determine the effect of simulated iceon the aerodynamic characteristics of the propeller. The irregular coat of cement and fabric was used on the blades to simulate in outline and thickness a formation of glaze ice that might be formed in flight. The propellers were tested on a new 2000-horsepower dynamometer, a brief description of which is included. All tests were made at a rotational speed of 1800 rpm for blade angles of 20, 25, 35, and 40 degrees at the 42-inch radius and at airspeeds varying from 120 to 420 miles per hour. The results are representative of full-scale constant-speed propeller operation.

Investigation of the Effect of a Tip Modification and Thermal De-icing Air Flow on Propeller Performance

Investigation of the Effect of a Tip Modification and Thermal De-icing Air Flow on Propeller Performance PDF

Author: Blake W. Corson

Publisher:

Published: 1946

Total Pages: 56

ISBN-13:

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Aerodynamic tests of a 12.208-foot-diameter two-blade hollow steel propeller before and after alteration for thermal de-icing have been made in the Langley 16-foot high-speed tunnel to determine the effect of the alterations on propeller efficiency. The propeller, which had Clark Y blade sections, was tested on a 2000-horsepower dynamometer at blade angles ranging from about 25 degrees to 60 degrees at the 42-inch radius and at airspeeds varying from 100 to 425 miles per hour.

Tank Tests to Determine the Effect of Varying Design Parameters of Planing-tail Hulls

Tank Tests to Determine the Effect of Varying Design Parameters of Planing-tail Hulls PDF

Author: John R. Dawson

Publisher:

Published: 1946

Total Pages: 582

ISBN-13:

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The second part of a series of tests made in Langley tank no. 2 to determine the effect of varying design parameters of planing-tail hulls is presented. Results are given to show the effects on resistance characteristics of varying angle of afterbody keel, depth of step, and length of afterbody chine. The effect of varying the gross load is shown for one configuration. The resistance characteristics of planing-tail hulls are compared withthose of a conventional flying-boat hull. The forces on the forebody and afterbody of one configuration are compared with the forces on a conventional hull.

An Evalution of Some Approximate Methods of Computing Landing Stresses in Aircraft

An Evalution of Some Approximate Methods of Computing Landing Stresses in Aircraft PDF

Author: Elbridge Z. Stowell

Publisher:

Published: 1948

Total Pages: 748

ISBN-13:

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The landing of a simplified airplane structure, consisting of a uniform beam for the wings, a concentrated mass for the fuselage, and a linear spring for the landing gear, is analyzed exactly and is compared with several approximate solutions. The approximate solutions which neglect elasticity in the determination of landing-gear reaction but consider elasticity in computations of stresses give results of good accuracy and indicate that drop tests in which rigid masses are used may be a satisfactory approach to the landing problem.

Wartime Report

Wartime Report PDF

Author:

Publisher:

Published: 194?

Total Pages: 796

ISBN-13:

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Reproductions of reports, some declassified, of research done at Langley Memorial Aeronautical Laboratory during World War II. The order of reports does not represent when they were chronologically issued. Reference to the original version of each report is included.

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