Effect of Airfoil Profile of Symmetrical Sections on the Low-speed Rolling Derivatives of 45© Sweptback-wing Models of Aspect Ratio 2.61 PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Effect of Airfoil Profile of Symmetrical Sections on the Low-speed Rolling Derivatives of 45© Sweptback-wing Models of Aspect Ratio 2.61 PDF full book. Access full book title Effect of Airfoil Profile of Symmetrical Sections on the Low-speed Rolling Derivatives of 45© Sweptback-wing Models of Aspect Ratio 2.61 by William Letko. Download full books in PDF and EPUB format.
Author: William Letko
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 34
Get Book Here
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.
Author: William Letko
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 34
Get Book Here
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.
Author: William Letko
Publisher:
ISBN:
Category :
Languages : en
Pages : 17
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 36
Get Book Here
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.
Author: William Letko
Publisher:
ISBN:
Category :
Languages : en
Pages : 21
Get Book Here
Book Description
Author: Jack Fischel
Publisher:
ISBN:
Category : Ailerons
Languages : en
Pages : 44
Get Book Here
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.
Author: William Solomon
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 44
Get Book Here
Book Description
Author: Donald E. Hewes
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 36
Get Book Here
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: George L. Pratt
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 110
Get Book Here
Book Description
Author: Boyd C. Myers
Publisher:
ISBN:
Category : Airplane
Languages : en
Pages : 36
Get Book Here
Book Description
This paper presents the results of the investigation of a wing-alone and wing-fuselage configuration employing a wing with the quarter-chord line swept back 45 degrees, with aspect ratio 4, taper ratio 0.3, and an NACA 65A006 airfoil section. Lift, drag, pitching moment, and root bending moment were obtained for these configurations. In addition, effective downwash angles and dynamic-pressure characteristics in the region of a probable tail location were also obtained for these configurations and are presented for a range of tail heights at one tail length. In order to expedite the publishing of these data, only a brief analysis is included.
Author: John C. Heitmeyer
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 30
Get Book Here
Book Description
