Author : William Letko
Publisher :
Page : 21 pages
File Size : 44,55 MB
Release : 1948
Category :
ISBN :
Author : William Letko
Publisher :
Page : 34 pages
File Size : 23,3 MB
Release : 1949
Category : Airplanes
ISBN :
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 :
Page : 17 pages
File Size : 17,35 MB
Release : 1949
Category :
ISBN :
Author : United States. National Advisory Committee for Aeronautics
Publisher :
Page : 274 pages
File Size : 34,31 MB
Release : 1953
Category : Aeronautics
ISBN :
Author :
Publisher :
Page : 750 pages
File Size : 36,83 MB
Release : 1949
Category : Aeronautics
ISBN :
Author : George L. Pratt
Publisher :
Page : 110 pages
File Size : 45,43 MB
Release : 1952
Category : Airplanes
ISBN :
Author : Jacob H. Lichtenstein
Publisher :
Page : 40 pages
File Size : 15,14 MB
Release : 1951
Category : Airplanes
ISBN :
Wind-tunnel results of the effects of horizontal-tail size and length on the low-speed static longitudinal stability and the steady-state rotary damping in pitch for a complete model with wing and tail surfaces having the quarter-chord lines swept back 45 degrees and aspect ratios of 4 are presented.
Author : William Letko
Publisher :
Page : 20 pages
File Size : 15,80 MB
Release : 1948
Category : Airplanes
ISBN :
This report presents the results of an investigation made in the Langley stability tunnel for determining the effects of taper ratio on the static and yawing stability derivatives of wings having their quarter-chord lines sweptback 45 degrees. All the wings had aspect ratios of 2.61 and had NACA 0012 airfoil sections normal to the quarter-chord lines. Taper ratios of 1.00, 0.50, and 0.25 were investigated. The experimental results are compred with available theory.
Author :
Publisher :
Page : 29 pages
File Size : 34,48 MB
Release : 1948
Category : Airplanes
ISBN :
This report contains the results of wind-tunnel tests to determine the effect of dihedral on the static-stability and yawing derivatives of 45 degree sweptback-wing model of aspect ratio 2.61. The tests were made in the curved-flow test section of the Langley stability tunnel at a Reynolds number of approximately 1,100,000 and consisted of force measurements throughout the lift-coefficient range.
Author : Jack Fischel
Publisher :
Page : 44 pages
File Size : 44,88 MB
Release : 1951
Category : Ailerons
ISBN :
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.
