Author : Roger G. Hart
Publisher :
Page : 42 pages
File Size : 23,51 MB
Release : 1949
Category : Body of revolution
ISBN :
Author :
Publisher :
Page : 198 pages
File Size : 37,36 MB
Release : 1961
Category : Aerodynamics
ISBN :
Author : United States. National Advisory Committee for Aeronautics
Publisher :
Page : 860 pages
File Size : 41,95 MB
Release : 1957
Category : Aeronautics
ISBN :
Author :
Publisher :
Page : 818 pages
File Size : 12,14 MB
Release : 1954
Category : Aeronautics
ISBN :
Author : William E. Stoney
Publisher :
Page : 196 pages
File Size : 48,54 MB
Release : 1961
Category : Body of revolution
ISBN :
This report presents a compilation of most of the zero-lift drag results obtained from free-flight measurements made by the Langley Pilotless Aircraft Research Division on fin-stabilized bodies of revolution. The data are arranged on standard forms, which also contain the significant geometrical factors. Supplementary data have been provided to facilitate the determination of the body pressure drags from the measurement total drags. Summary plots and discussions have been included to provide a unified and broad picture of the effects of the body geometry on zero-lift drag.
Author : United States. National Advisory Committee for Aeronautics
Publisher :
Page : 716 pages
File Size : 26,92 MB
Release : 1958
Category : Aeronautics
ISBN :
Author : United States. National Advisory Committee for Aeronautics
Publisher :
Page : 568 pages
File Size : 27,53 MB
Release : 1951
Category : Aeronautics
ISBN :
Author :
Publisher :
Page : 1878 pages
File Size : 33,15 MB
Release : 1961
Category : Government publications
ISBN :
Author : United States. National Advisory Committee for Aeronautics
Publisher :
Page : 508 pages
File Size : 46,68 MB
Release : 1954
Category : Aeronautics
ISBN :
Author : Harold L. Crane
Publisher :
Page : 654 pages
File Size : 50,35 MB
Release : 1958
Category : Airplanes
ISBN :
A flight investigation at subsonic speeds of a method to improve the damping of lateral oscillations by means of a viscous damping cylinder used in the rudder system in conjunction with adjusted hinge-moment parameters has been conducted. The damping device has been applied to a modern fighter-type jet-powered airplane. The rudder was made to float with the relative wind by the addition of trailing-edge strips. In order to amplify the floating tendency (by reducing the restoring moment), a highly geared balancing tab was incorporated. Lag of the motion of the free rudder with respect to the yawing of the airplane was introduced by means of a small viscous damping cylinder linked to the rudder.
