Effects of Wing Position and Fuselage Size on the Low-speed Static and Rolling Stability Characteristics of a Delta-wing Model PDF Download
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Author: Alex Goodman
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 82
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Book Description
An investigation was made to determine the effects of wing position and fuselage size on the low-speed static and rolling stability characterististics of airplane models having a triangular wing and vertical tail surfaces.
Author: Alex Goodman
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 82
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Book Description
An investigation was made to determine the effects of wing position and fuselage size on the low-speed static and rolling stability characterististics of airplane models having a triangular wing and vertical tail surfaces.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 404
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Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 580
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Book Description
Author: Kenneth P. Spreemann
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 644
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Book Description
This investigation was made to determine the effects of 6 degree full-span and 3 degree partial-span leading-edge flaps in combination with chord-extensions or fences on the aerodynamic characteristics of a wing-fuselage configuration with a 45 degree sweptback wing of aspect ratio 4, taper ratio 0.3, and NACA 65A006 airfoil sections. The investigation was made in the Langley high-speed 7- by 10-foot tunnel over a Mach number range of 0.40 to 0.93 and an angle-of-attack range of about -2 degrees to 24 degrees. Lift, drag, and pitching-moment data were obtained for all configurations. From overall considerations of stability and performance it appears that with the model of this investigation the 6 degree full-span leading-edge flaps in combination with the chord-extension over the outboard 35 percent of the span, with or without leading-edge camber, would be the most desirable configuration.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 750
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Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 46
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Book Description
Author: Paul Kuhn
Publisher:
ISBN:
Category : Boxes
Languages : en
Pages : 632
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Book Description
A method is presented for calculating the stresses produced by rectangular cutouts of any size in torsion boxes. The problem is divided into a "box problem" and a "cover problem." The box problem is a special case of the general method of analyzing torsion boxes without cutouts. In the cover problem, simple shear-lag theory is used to obtain "key" stresses; the final distributions are obtained from these key stresses by means of simple rules or empirical distribution curves. Comparisons with the results from three series of tests in which the dimensions of the cutouts varied over a wide range are shown.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 468
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Book Description
Author: Defense Documentation Center (U.S.)
Publisher:
ISBN:
Category : Industrial arts
Languages : en
Pages : 922
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 950
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Book Description
