Author: Robert William Fralich
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 652
Book Description
A flutter analysis, employing slender-body aerodynamic theory and thin-plate theory, is made for rectangular wings of very low aspect ratio with a constant thickness. The spanwise variation of wing deflection is assumed to be given by a parabola, and the chordwise variation is allowed complete freedom. The results show the vsriation of flutter speed and male shape with aspect ratio. Comparisons are made with additional resuits obtained by approximating the chordwise deflection shape by use of parabolic or cubic curves. The analysis shows that the cubic approximation gives good resuits for a ratio of chord to semispan less than 3.
Flutter Analysis of Rectangular Wings of Very Low Aspect Ratio
Author: Robert William Fralich
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 652
Book Description
A flutter analysis, employing slender-body aerodynamic theory and thin-plate theory, is made for rectangular wings of very low aspect ratio with a constant thickness. The spanwise variation of wing deflection is assumed to be given by a parabola, and the chordwise variation is allowed complete freedom. The results show the vsriation of flutter speed and male shape with aspect ratio. Comparisons are made with additional resuits obtained by approximating the chordwise deflection shape by use of parabolic or cubic curves. The analysis shows that the cubic approximation gives good resuits for a ratio of chord to semispan less than 3.
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 652
Book Description
A flutter analysis, employing slender-body aerodynamic theory and thin-plate theory, is made for rectangular wings of very low aspect ratio with a constant thickness. The spanwise variation of wing deflection is assumed to be given by a parabola, and the chordwise variation is allowed complete freedom. The results show the vsriation of flutter speed and male shape with aspect ratio. Comparisons are made with additional resuits obtained by approximating the chordwise deflection shape by use of parabolic or cubic curves. The analysis shows that the cubic approximation gives good resuits for a ratio of chord to semispan less than 3.
Flutter of a Low-aspect-ratio Rectangular Wing
Author: Stanley R. Cole
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 24
Book Description
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 24
Book Description
Flutter and Divergence of Rectangular Wings of Very Low Aspect Ratio
Author: Robert W. Fralich
Publisher:
ISBN:
Category :
Languages : en
Pages : 15
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 15
Book Description
Formulation of a Structural Model for Flutter Analysis of Low Aspect Ratio Composite Aircraft Wings
Author: Timothy J. Seitz
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 164
Book Description
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 164
Book Description
Technical Note - National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 966
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 966
Book Description
Flutter of Low Aspect-ratio Wings: Calculation of pressure distribution for oscillating wings of arbitrary planform in subsonic flow by the kernel-function methods, by Pao-Tan Hsu
Author: Massachusetts Institute of Technology
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 60
Book Description
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 60
Book Description
Flutter at Very High Speeds
Author: Harry L. Runyan
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 16
Book Description
This paper is concerned with a discussion of some of the problems of flutter and aeroelasticity that are or may be important at high speeds. Various theoretical procedures for treating high Mach number flutter are reviewed. Application of two of these methods, namely, the Van Dyke method and piston-theory method, is made to a specific example and compared with linear two- and three-dimensional results. It is shown that the effects of thickness and airfoil shape are destabilizing as compared with linear theory at high Mach number. In order to demonstrate the validity of these large predicted effects, experimental flutter results are shown for two rectangular wings at Mach numbers of 6.86 and 3. The results of nonlinear piston-theory calculations were in good agreement with experiment, whereas the results of using two- and three-dimensional linear theory were not. In addition, some results demonstrating the importance of including camber modes in a flutter analysis are shown, as well as a discussion of one case of flutter due to aerodynamic heating.
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 16
Book Description
This paper is concerned with a discussion of some of the problems of flutter and aeroelasticity that are or may be important at high speeds. Various theoretical procedures for treating high Mach number flutter are reviewed. Application of two of these methods, namely, the Van Dyke method and piston-theory method, is made to a specific example and compared with linear two- and three-dimensional results. It is shown that the effects of thickness and airfoil shape are destabilizing as compared with linear theory at high Mach number. In order to demonstrate the validity of these large predicted effects, experimental flutter results are shown for two rectangular wings at Mach numbers of 6.86 and 3. The results of nonlinear piston-theory calculations were in good agreement with experiment, whereas the results of using two- and three-dimensional linear theory were not. In addition, some results demonstrating the importance of including camber modes in a flutter analysis are shown, as well as a discussion of one case of flutter due to aerodynamic heating.
Technical Note
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 790
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 790
Book Description
Flutter Investigation of Two Thin, Low-aspect-ratio, Swept, Solid, Metal Wings in the Transonic Range by Use of Free-falling Body
Author: W. T. Lauten
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 18
Book Description
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 18
Book Description
Effect of Aspect Ratio on Undamped Torsional Oscillations of a Thin Rectangular Wing in Supersonic Flow
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.
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.