Effect of Airfoil Profile of Symmetrical Sections on the Low-speed Rolling Derivatives of 45© Sweptback-wing Models of Aspect Ratio 2.61

Effect of Airfoil Profile of Symmetrical Sections on the Low-speed Rolling Derivatives of 45© Sweptback-wing Models of Aspect Ratio 2.61 PDF Author: William Letko
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 34

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Book Description
An investigation was made in the Langley stability tunnel to determine the effect of airfoil profile of symmetrical sections on the rolling derivatives of three untapered wings having 45 deg sweepback. The wings had the following profiles normal to the leading edge: biconvex (12% thick), NACA 65 sub 1 -012, and NACA 0012. The AR for each wing was 2.61. Calculations were made to determine the effect of different wing profiles on the stability boundaries and motions at subsonic speeds of a typical transonic airplane configuration. Results indicate that increasing the sharpness of the leading edge of the airfoil decreased the range of lift coefficients over which the derivatives maintained their initial trends and usually decreased the maximum values of the derivatives obtained in the unstalled range. Results of the calculations of the dynamic stability of the airplane configuration show only small changes in stability due to changes in airfoil profile.

Effect of Airfoil Profile of Symmetrical Sections on the Low-speed Rolling Derivatives of 45 Degrees Sweptback-wing Models of Aspect Ratio 2.61

Effect of Airfoil Profile of Symmetrical Sections on the Low-speed Rolling Derivatives of 45 Degrees Sweptback-wing Models of Aspect Ratio 2.61 PDF Author: William Letko
Publisher:
ISBN:
Category :
Languages : en
Pages : 17

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Book Description

Effect of Airfoil Profile of Symmetrical Sections on the Low-Speed Rolling Derivatives of 45 Deg Sweptback-Wing Models of Aspect Ratio 2.61

Effect of Airfoil Profile of Symmetrical Sections on the Low-Speed Rolling Derivatives of 45 Deg Sweptback-Wing Models of Aspect Ratio 2.61 PDF Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 36

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Book Description
An investigation was made in the Langley stability tunnel to determine the effect of airfoil profile of symmetrical sections on the rolling derivatives of three untapered wings having 45 deg sweepback. The wings had the following profiles normal to the leading edge: biconvex (12% thick), NACA 65 sub 1 -012, and NACA 0012. The AR for each wing was 2.61. Calculations were made to determine the effect of different wing profiles on the stability boundaries and motions at subsonic speeds of a typical transonic airplane configuration. Results indicate that increasing the sharpness of the leading edge of the airfoil decreased the range of lift coefficients over which the derivatives maintained their initial trends and usually decreased the maximum values of the derivatives obtained in the unstalled range. Results of the calculations of the dynamic stability of the airplane configuration show only small changes in stability due to changes in airfoil profile.

Effect of Airfoil Profile of Symmetrical Sections on the Low-speed Static-stability and Yawing Derivatives of 45 Degree Sweptback Wing Models of Aspect Ratio 2.61

Effect of Airfoil Profile of Symmetrical Sections on the Low-speed Static-stability and Yawing Derivatives of 45 Degree Sweptback Wing Models of Aspect Ratio 2.61 PDF Author: William Letko
Publisher:
ISBN:
Category :
Languages : en
Pages : 21

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Effect of Aspect Ratio and Sweepback on the Low-speed Lateral Control Characteristics of Untapered Low-aspect-ratio Wings Equipped with Retractable Ailerons

Effect of Aspect Ratio and Sweepback on the Low-speed Lateral Control Characteristics of Untapered Low-aspect-ratio Wings Equipped with Retractable Ailerons PDF Author: Jack Fischel
Publisher:
ISBN:
Category : Ailerons
Languages : en
Pages : 44

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Book Description
Results and discussion are presented of a low-speed lateral-control investigation of three untapered unswept wings of aspect ratio 1.13, 2.13, and 4.13 and an untapered 45 degrees sweptback wing of aspect ratio 2.09 equipped with 0.60-semispan retractable ailerons having various projections. Continuous-span ailerons were tested at outboard stations on the unswept wings, and plain (continuous span) and stepped (segmented) ailerons were tested at various spanwise stations with and without simulated actuating arms on the sweptback wing.

Effect of Longitudinal Wings Position on the Pressure Characteristics at Transonic Speeds of a 45© Sweptback Wing-fuselage Model

Effect of Longitudinal Wings Position on the Pressure Characteristics at Transonic Speeds of a 45© Sweptback Wing-fuselage Model PDF Author: William Solomon
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 44

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Book Description

Effects of Twist and Camber on the Low-speed Longitudinal Stability Characteristics of a 45© Swept-back Wing of Aspect Ratio 8 at Reynolds Numbers from 1.5 X 106 to 4.8 X 10 as Determined by Pressure Distributions, Force Tests, and Calculations

Effects of Twist and Camber on the Low-speed Longitudinal Stability Characteristics of a 45© Swept-back Wing of Aspect Ratio 8 at Reynolds Numbers from 1.5 X 106 to 4.8 X 10 as Determined by Pressure Distributions, Force Tests, and Calculations PDF Author: George L. Pratt
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 110

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Book Description

Effects of Twist and Camber on the Low-speed Characteristics of a Large-scale 45 Degree Swept-back Wing

Effects of Twist and Camber on the Low-speed Characteristics of a Large-scale 45 Degree Swept-back Wing PDF Author: Lynn W. Hunton
Publisher:
ISBN:
Category :
Languages : en
Pages : 36

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Book Description

Effect of Reynolds Number on the Lateral-stability Derivatives at Low Speed of Swept-back and Delta-wing-fuselage Combinations Oscillating in Yaw

Effect of Reynolds Number on the Lateral-stability Derivatives at Low Speed of Swept-back and Delta-wing-fuselage Combinations Oscillating in Yaw PDF Author: Charles P. Llewellyn
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 50

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Book Description
An investigation has been made to determine the effect of Reynolds number on the lateral-stability derivatives at low speed of sweptback- and delta-wing-fuselage combinations. Results were obtained from the models oscillating in yaw over an angle-of-attack ...

The Effects of Mass Distribution on the Low-speed Dynamic Lateral Stability and Control Characteristics of a Model with a 45° Sweptback Wing

The Effects of Mass Distribution on the Low-speed Dynamic Lateral Stability and Control Characteristics of a Model with a 45° Sweptback Wing PDF 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.