Author: Albert A. Schy
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 316
Book Description
Hydrodynamic Impact of a System with a Single Elastic Mode
Author: Albert A. Schy
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 316
Book Description
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 316
Book Description
Index of NACA Technical Publications
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 274
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 274
Book Description
Annual Report of the National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1200
Book Description
Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1200
Book Description
Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
Report - National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1208
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1208
Book Description
Technical Note - National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1076
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1076
Book Description
Report
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 36
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 36
Book Description
Report
Simplified Procedures and Charts for the Rapid Estimation of Bending Frequencies of Rotating Beams
Author: Robert T. Yntema
Publisher:
ISBN:
Category : Bars (Engineering)
Languages : en
Pages : 692
Book Description
A more exact mode-expansion method used in evaluating the Rayleigh approach is also described. Numerous mode shapes and derivatives obtained in conjunction with the frequency calculations are presented in tabular form.
Publisher:
ISBN:
Category : Bars (Engineering)
Languages : en
Pages : 692
Book Description
A more exact mode-expansion method used in evaluating the Rayleigh approach is also described. Numerous mode shapes and derivatives obtained in conjunction with the frequency calculations are presented in tabular form.
Technical Note
Subsonic Flight Investigation of Methods to Improve the Damping of Lateral Oscillations by Means of a Viscous Damper in the Rudder System in Conjuction with Adjusted Hinge-moment Parameters
Author: Harold L. Crane
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 654
Book Description
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.
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 654
Book Description
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.