Stability and Control Characteristics at Low Speed of an Airplane Model Having a 38.7 Degree Sweptback Wing with Aspect Ratio 4.51, Taper Ratio 0.54, and Conventional Tail Surfaces PDF Download
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Author: Vernard E. Lockwood
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 155
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Book Description
Contains the results of a low-speed wind-tunnel investigation to determine the static stability and control characteristics of an airplane model having a leading-edge sweep of 38.7 degrees, aspect ratio of 4.51, and a taper ratio of 0.54. In addition to the complete model investigation the effects of leading edges slots, a circular-arc wing, drooped leading edges, change of tail length, and change of fin area on the aerodynamic characteristics were determined. Also includes an analysis of wing-fuselage interference effect on effective dihedral.
Author: Vernard E. Lockwood
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 155
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Book Description
Contains the results of a low-speed wind-tunnel investigation to determine the static stability and control characteristics of an airplane model having a leading-edge sweep of 38.7 degrees, aspect ratio of 4.51, and a taper ratio of 0.54. In addition to the complete model investigation the effects of leading edges slots, a circular-arc wing, drooped leading edges, change of tail length, and change of fin area on the aerodynamic characteristics were determined. Also includes an analysis of wing-fuselage interference effect on effective dihedral.
Author: Vernard E. Lockwood
Publisher:
ISBN:
Category :
Languages : en
Pages : 155
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Book Description
Author: Kenneth W. Goodson
Publisher:
ISBN:
Category :
Languages : en
Pages : 72
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Author: Joseph Weil
Publisher:
ISBN:
Category :
Languages : en
Pages : 84
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Book Description
Author: Marvin Schuldenfrei
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 86
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Book Description
An investigation has been made of a complete airplane model having a wing with the quarter-chord line swept back 40 degrees, aspect ratio 2.50, and taper ratio 0.42 to determine its low-speed stability and control characteristics. The longitudinal stability investigation included stabilizer and tail-off tests with different wing dihedral angles over an angle of attack range for the cruising and landing configurations and tests with a high horizontal-tail location for the cruising configuration. Tests were made of the wing along and to determine the effect of wing end plates in pitch. Lateral stability characteristics were determined for the airplane with different geometric wing dihedrals, with end plates, and with several dorsal modifications. Tests were made with ailerons and spoilers to determine control characteristics.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 88
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Book Description
Author: John C. McFall
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 44
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Author: Jacob H. Lichtenstein
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 34
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Book Description
Wind-tunnel results are presented to show the effect of changes in horizontal-tail location on the low-speed static longitudinal stability and steady-state rotary damping in pitch for a complete model with wing and tail surfaces having the quarter-chord lines swept back 45 degrees.
Author: Kenneth W. Goodson
Publisher:
ISBN:
Category : Stability of airplanes, Longitudinal
Languages : en
Pages : 64
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Book Description
An investigation was made at high subsonic speeds of a complete model having a highly tapered wing and several tail configurations. The basic aspect-ratio-4.00 wing had a zero taper and an unswept 0.80 chord line. Several aspect-ratio modifications to the basic wing were made by clipping off portions of the wing tips. The complete model was tested with a chord-plane tail, a T-tail, and a biplane tail (combined T-tail and chord-plane tail). The model was tested in the Langley high-speed 7- by 10-foot tunnel at Mach numbers from 0.60 to 0.92. The data show that, when reduced to the same static margin, all the tail configurations tested on the model provided fairly good stability characteristics, the biplane tail giving the best overall characteristics as regards pitching-moment linearity. Changes in static margin at zero lift coefficient with Mach number were small for the model with these tails over the Mach number range investigated.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 101
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Book Description
