The Pressure Distribution Over the Horizontal Tail Surfaces of an Airplane PDF Download
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Author: F. H. Norton
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 180
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Book Description
Author: F. H. Norton
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 180
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Book Description
Author: Frederick Harwood Norton
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 27
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Book Description
Author: F. H. Norton
Publisher:
ISBN:
Category :
Languages : en
Pages : 26
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Book Description
Author: F. H. Norton
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 86
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Book Description
Author: F. H. Norton
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 40
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Book Description
Author: Melvin Sadoff
Publisher:
ISBN:
Category : Fighter planes
Languages : en
Pages : 17
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Book Description
Measurements were made in sideslipping flight at a Mach number of 0.50 of the pressure distribution over the horizontal tail surfaces of a tractor-propeller-driven pursuit airplane, to determine the effects of angle of sideslip and propeller operation on the tail-load distribution. Measurements were also made on the tail-load distribution on the horizontal tail in steady unaccelerated flight over a Mach number range of 0.30 to 0.79 and 0.30 to 0.74, respectively, for the power-on and power-off conditions.
Author: Richard V. Rhode
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 20
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Book Description
Author: A. M. Rothrock
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 204
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Book Description
Author: Melvin Sadoff
Publisher:
ISBN:
Category : Compressibility
Languages : en
Pages : 29
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Book Description
Pressure-distribution measurements were made in steady straight and accelerated flight over both sides of the horizontal-tail surface of a typical pursuit airplane up to a Mach number of 0.79. The results showed that a sharply increasing down-load was required to balance the increased diving moment of the wing-fuselage-propeller group at Mach numbers above about 0.70. There was little change, up to a Mach number of about 0.65, of the tail-load gradient (rate of increase of tail load for a unit change in acceleration factor); beyond that Mach number, however, a rapid decrease of tail-load gradient to a Mach number of about 0.73 and then a very sharp increase up to a Mach number of 0.785 was noted. The root bending moments increased considerably on the right tail and decreased, to a lesser extent, on the left tail at the higher Mach numbers, resulting in increased fuselage torsional moments at high speeds. At the higher values of lift coefficient (0.5 to 0.8), there was little change of the lateral distance to the center pressure up to a Mach number of about 0.73; at the highest speed and at low lift coefficients (0 to 0.1) the center of pressure was inboard approximately 3 feet on the left tail and 1.5 feet on the right tail as compared with the values at lower speeds. It appears that satisfactory quantitative data on total tail loads may be obtained from measurements at four stations, equally spaced along the entire tail span.
Author: John Boshar
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 22
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Book Description
Results are presented of pressure-distribution measurements taken over the horizontal tail surfaces of a Curtiss P-40K airplane during several low-speed pull-ups to abrupt stall in which tail buffeting was experienced.
