Effect of High-lift Devices on the Low-speed Static Lateral and Yawing Stability Characteristics of an Untapered 45 Degree Sweptback Wing PDF Download
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Author: Jacob H. Lichenstein
Publisher:
ISBN:
Category :
Languages : en
Pages : 21
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Book Description
Author: Jacob H. Lichenstein
Publisher:
ISBN:
Category :
Languages : en
Pages : 21
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Book Description
![Effect of High-lift Devices on the Low-speed Static Lateral and Yawing Stability Characteristics of an Untapered 45 [degrees] Sweptback Wing PDF](https://books.google.com/books/content/images/frontcover/GJ25tgAACAAJ?fife=w80-h100)
Author: Jacob H. Lichtenstein
Publisher:
ISBN:
Category :
Languages : en
Pages : 20
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Book Description
Author: Jacob H. Lichtenstein
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 20
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Book Description
Results of a low-speed wind-tunnel investigation to determine the effect of high-lift devices on the static lateral stability derivatives and the yawing derivatives of an untapered 45 degree sweptback wing are presented. The tests were made in the curved-flow test section of the Langley stability tunnel at a Reynolds number of 1,100, 000.
Author: William Letko
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 58
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Book Description
Contains wind-tunnel results of an investigation made in the Langley stability tunnel to determine the effects of vertical-tail area and length on the low-speed yawing derivatives of a midwing airplane model having a 45 degree sweptback wing and tail surfaces. Comparisons of the measured contributions with those calculated by currently available procedures are also presented. The interference between the various model components is discussed.
Author:
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 626
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Author: Donald E. Hewes
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 36
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Book Description
The trends in lateral stability and control produced variations of the mass distribution were determined for a model with a 45 degree sweptback wing. Calculations were made to correlate the trends determined by theory with those determined from tests of a free-flying dynamic model in the Langley free-flight tunnel.
Author: Jacob H. Lichtenstein
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 49
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Book Description
This paper contains the results of wind-tunnel tests to determine the effects of plain and split trailing edge flaps, with and without leading-edge slats, on the low-speed static-lateral-stability derivatives of a 45 degree sweptback-wing-body configuration. Comparisons between the increments obtained from experiment and those evaluated by simple sweep theory in combination with measured lift and drag increments are also made.
![Effect of High-lift Devices on the Static-lateral-stability Derivatives of a 45 [degrees] Sweptback Wing of Aspect Ratio 4.0 and Taper Ratio 0.6 in Combination with a Body PDF](https://books.google.com/books/content/images/frontcover/QgHOtgAACAAJ?fife=w80-h100)
Author: Jacob H. Lichtenstein
Publisher:
ISBN:
Category :
Languages : en
Pages : 50
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 52
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Book Description
An investigation has been made in the Langley stability tunnel to determine the effect of high-lift devices on the low-speed static-lateral-stability derivatives of a 45 deg sweptback wing of aspect ratio 4.0 and taper ratio 0.6. Comparison between the increments in the static-lateral-stability derivatives due to flap deflection obtained from experiment and the increments evaluated by a simple sweep theory is also made. The results of the investigation show that, for moderate and high lift coefficients, an increase in trailing-edge flap span, with or without a leading-edge slat, generally resulted in increased effective dihedral and directional stability. The leading-edge slats tended mainly to extend the trends obtained at low lift coefficients for the dihedral effect to nearer maximum lift. An application of simple sweep theory and measured lift and drag increments to the evaluation of the increments in the static-lateral-stability derivatives due to trailing-edge flaps indicates that the trend and approximate magnitude of the variation of these increments with flap span are predicted in the moderate and high lift-coefficient range.
