Wind-tunnel Investigation of Rounded Horns and of Guards on a Horizontal Tail Surface PDF Download
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Author: Robert B. Liddell Publisher: ISBN: Category : Aerodynamics Languages : en Pages : 124
Book Description
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.
Author: Robert B. Liddell Publisher: ISBN: Category : Aerodynamics Languages : en Pages : 124
Book Description
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.
Author: Publisher: ISBN: Category : Aeronautics Languages : en Pages : 690
Book Description
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.
Author: Leland G. Desmon Publisher: ISBN: Category : Internal combustion engines Languages : en Pages : 530
Book Description
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.
Author: Robert B. Liddell
Author: Robert B. Liddell
Author: United States. National Advisory Committee for Aeronautics
Author: 
Author: United States. National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Author: 
Author: United States. National Advisory Committee for Aeronautics
Author: Leland G. Desmon
Author: United States. National Advisory Committee for Aeronautics