Effect of Aspect Ratio on Undamped Torsional Oscillations of a Thin Rectangular Wing in Supersonic Flow PDF Download
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Author: Charles E. Watkins Publisher: ISBN: Category : Aerodynamics, Supersonic Languages : en Pages : 42
Book Description
The velocity potential and aerodynamic-torsional moment coefficients based on the linearized equations of motion for small disturbances are derived for a rectangular wing by means of appropriate distributions of moving sources and doublets. The aerodynamic-torsional-moment coefficent to study the effect of aspect ratio on the undamped torsional oscillations of a finite rectangular wing. Decreasing the aspect ratio of the wing is found to have a highly stabilizing effect on the undamped torsional oscillations. The results of some selected calculations are presented in the figures that illustrate this fact.
Author: Charles E. Watkins Publisher: ISBN: Category : Aerodynamics, Supersonic Languages : en Pages : 42
Book Description
The velocity potential and aerodynamic-torsional moment coefficients based on the linearized equations of motion for small disturbances are derived for a rectangular wing by means of appropriate distributions of moving sources and doublets. The aerodynamic-torsional-moment coefficent to study the effect of aspect ratio on the undamped torsional oscillations of a finite rectangular wing. Decreasing the aspect ratio of the wing is found to have a highly stabilizing effect on the undamped torsional oscillations. The results of some selected calculations are presented in the figures that illustrate this fact.
Author: Robert T. Jones Publisher: ISBN: Category : Airplanes Languages : en Pages : 708
Book Description
The problem of the minimum induced drag of wings having a given lift and a given span is extended to include cases in which the bending moment to be supported by the wing is also given. Expressions for the spanwise load distribution and the minimum drag in terms of the lateral position of the load centroid are given. The results show a 15-percent reduction of the induced drag with a 15-percent increase in span over that for an elliptic loading having the same total lift and bending moment.
Author: Harvard Lomax Publisher: ISBN: Category : Boundary value problems Languages : en Pages : 48
Book Description
The problem of the build-u of lift on two- and three-dimensional wings flying at high speeds is discussed as a boundary-value problem for the classical wave equation. Kirchhoff's formula is applied so that the analysis is reduced, just as in the steady state, to an investigation of sources and doublets. Some simple applications of this method are considered, including the determination of the starting lift of a three-dimensional wing and the potential functions for some types of unsteady vortex motion.
Author: Lipman Bers Publisher: ISBN: Category : Aerofoils Languages : en Pages : 700
Book Description
The method of computing velocity and pressure distributions along wing profiles under the assumption of the simplified density-speed relation, outlined in NACA Technical Note 1006, is extended to the case of a nonsymmetrical profile and a flow with circulation. The shape of the profile, the speed of the undisturbed flow, and a parameter determing the angle of attack may be prescribed. The problem is reduced to a nonlinear integral equation which can be solved numerical by an iteration method. A numerical example is given.
Author: Charles E. Watkins
Author: Charles E. Watkins
Author: United States. National Advisory Committee for Aeronautics
Author: Robert T. Jones
Author: Harvard Lomax
Author: United States. National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Author: Lipman Bers
Author: 
Author: