Wind Tunnel Investigation of Effect of Yaw on Lateral-stability Characteristics PDF Download
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Author: Isidore G. Recant
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 36
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Book Description
Combinations of an NACA 23012 tapered wing and a circular fuselage having a wedge-shaped rear were tested in the NACA 7- by 10-foot wind tunnel to determine the effect of wing-fuselage interference on the lateral-stability of wing-fuselage interference on the lateral-stability characteristics. The model configurations represented a high-wing, a mid-wing, and a low-wing monoplane. For each configuration, tests were made with a partial-span split flap neutral and deflected 60 degrees and with and without a vertical tail. Tests of the fuselage alone and of the fuselage with the vertical tail were also made.
Author: Isidore G. Recant
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 36
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Book Description
Combinations of an NACA 23012 tapered wing and a circular fuselage having a wedge-shaped rear were tested in the NACA 7- by 10-foot wind tunnel to determine the effect of wing-fuselage interference on the lateral-stability of wing-fuselage interference on the lateral-stability characteristics. The model configurations represented a high-wing, a mid-wing, and a low-wing monoplane. For each configuration, tests were made with a partial-span split flap neutral and deflected 60 degrees and with and without a vertical tail. Tests of the fuselage alone and of the fuselage with the vertical tail were also made.
Author: Millard J. Bamber
Publisher:
ISBN:
Category :
Languages : en
Pages : 18
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Book Description
Author: Harold S. Johnson
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 26
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Author: M.J. Queijo
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 30
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Author: Thomas G. Gainer
Publisher:
ISBN:
Category :
Languages : en
Pages : 28
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Book Description
Author: James H. Henderson
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 872
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Book Description
Transonic wind tunnel tests were conducted on a sting-mounted model to determine thrust effects on longitudinal stability characteristics of several body-fin combinations. The plume was simulated by cold air ejected from a series of sonic jets normal to the missile axis. One fin configuration was tested at several longitudinal positions. Adverse plume effects on stability were reduced by location of fins a distance forward of the base. The test was conducted at the Calspan Corporations' 8 foot Transonic Wind Tunnel at Mach numbers ranging from 0.4 to 1.25. Angles of attack ranged from -4 degrees to 12 degrees. Data were also obtained at roll angles of 22.5 degrees and 45 degrees for one configuration.
Author: Thomas J. Jr King
Publisher:
ISBN:
Category :
Languages : en
Pages : 61
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Author: Raymond E. Mineck
Publisher:
ISBN:
Category :
Languages : en
Pages : 88
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Author: L. C. Garby
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 56
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 44
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