Wind-tunnel Investigation of Rounded Horns and of Guards on a Horizontal Tail Surface

Wind-tunnel Investigation of Rounded Horns and of Guards on a Horizontal Tail Surface

Author: Robert B. Liddell

Publisher:

Published: 1944

Total Pages: 124

ISBN-13:

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Summary: An investigation was made to determine the aerodynamic effects of horn balances with various plan forms and of guards on a horizontal tail surface. The results indicate that rounding the adjacent horn and stabilizer edges caused neglibible changes in the aerodynamic characteristics, except for the changes resulting from the decrease in the area momeent of the horn. The use of guards mounted between the stabilizer and horn was found to increase the slope of the lift curves with angle of attack or with elevator deflection. The negative slopes of the curves of hinge moment against angle of attack and elevator deflection increased as the guard area was increased.


Wartime Report

Wartime Report

Author: United States. National Advisory Committee for Aeronautics

Publisher:

Published:

Total Pages: 294

ISBN-13:

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Wartime Report

Wartime Report

Author:

Publisher:

Published: 194?

Total Pages: 690

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.


Effect of Exhaust Pressure on the Performance of a 12-cylinder Liquid-cooled Engine

Effect of Exhaust Pressure on the Performance of a 12-cylinder Liquid-cooled Engine

Author: Leland G. Desmon

Publisher:

Published: 1947

Total Pages: 530

ISBN-13:

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A dynamometer-stand investigation was conducted to determine the effect of exhaust pressure on the performance of a 12-cylinder liquid-cooled aircraft engine equipped with a conventional exhaust collector. The investigation covered a range of exhaust pressures from about 7 to approximately 62 inches of mercury absolute, engine speeds from 1600 to 3000 rpm, inlet-manifold pressures from 30 to 50 inches of mercury absolute and fuel-air ratios of 0.063, 0.069, 0.085, and 0.100.