Preliminary Investigation at Low Speeds of Swept Wings in Rolling Flow
Author: David Feigenbaum
Publisher:
Published: 1947
Total Pages: 36
ISBN-13:
DOWNLOAD EBOOKRead and Download eBook Full
Author: David Feigenbaum
Publisher:
Published: 1947
Total Pages: 36
ISBN-13:
DOWNLOAD EBOOKAuthor:
Publisher:
Published: 1948
Total Pages: 24
ISBN-13:
DOWNLOAD EBOOKAuthor: United States. National Advisory Committee for Aeronautics
Publisher:
Published: 1959
Total Pages: 388
ISBN-13:
DOWNLOAD EBOOKAuthor: William Letko
Publisher:
Published: 1949
Total Pages: 34
ISBN-13:
DOWNLOAD EBOOKAn 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:
Published: 1949
Total Pages: 750
ISBN-13:
DOWNLOAD EBOOKAuthor:
Publisher:
Published: 1956
Total Pages: 2126
ISBN-13:
DOWNLOAD EBOOKAuthor: United States. National Advisory Committee for Aeronautics
Publisher:
Published: 1952
Total Pages: 812
ISBN-13:
DOWNLOAD EBOOK