Preliminary Investigation at Low Speeds of Swept Wings in Rolling Flow 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 Preliminary Investigation at Low Speeds of Swept Wings in Rolling Flow PDF full book. Access full book title Preliminary Investigation at Low Speeds of Swept Wings in Rolling Flow by David Feigenbaum. Download full books in PDF and EPUB format.
Author: David Feigenbaum
Publisher:
ISBN:
Category : Air flow
Languages : en
Pages : 36
Get Book Here
Book Description
Author: David Feigenbaum
Publisher:
ISBN:
Category : Air flow
Languages : en
Pages : 36
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 24
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 616
Get Book Here
Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 388
Get Book Here
Book Description
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:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 34
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 750
Get Book Here
Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 812
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 2126
Get Book Here
Book Description
Author: Douglas Aircraft Company
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 684
Get Book Here
Book Description
