scholarly journals Asymptotic Representations for Root Vectors of Nonselfadjoint Operators and Pencils Generated by an Aircraft Wing Model in Subsonic Air Flow

2001 ◽  
Vol 260 (2) ◽  
pp. 341-366 ◽  
Author(s):  
Marianna A. Shubov
Keyword(s):  
Air Flow ◽  
Aircraft Wing ◽  
Wing Model ◽  
Asymptotic Representations

scholarly journals On fluttering modes for aircraft wing model in subsonic air flow

2014 ◽  
Vol 470 (2172) ◽  
pp. 20140582 ◽  
Author(s):  
Marianna A. Shubov
Keyword(s):  
Air Flow ◽  
Spectral Characteristics ◽  
Reduced Model ◽  
Mode Shapes ◽  
Model Parameters ◽  
Aircraft Wing ◽  
Generalized Resolvent ◽  
Wing Model ◽  
The Laplace Transform ◽  
Two Parameter

The paper deals with unstable aeroelastic modes for aircraft wing model in subsonic, incompressible, inviscid air flow. In recent author’s papers asymptotic, spectral and stability analysis of the model has been carried out. The model is governed by a system of two coupled integrodifferential equations and a two-parameter family of boundary conditions modelling action of self-straining actuators. The Laplace transform of the solution is given in terms of the ‘generalized resolvent operator’, which is a meromorphic operator-valued function of the spectral parameter λ, whose poles are called the aeroelastic modes. The residues at these poles are constructed from the corresponding mode shapes. The spectral characteristics of the model are asymptotically close to the ones of a simpler system, which is called the reduced model. For the reduced model, the following result is shown: for each value of subsonic speed, there exists a radius such that all aeroelastic modes located outside the circle of this radius centred at zero are stable. Unstable modes, whose number is always finite, can occur only inside this ‘circle of instability’. Explicit estimate of the ‘instability radius’ in terms of model parameters is given.

scholarly journals Numerical Investigation of Aeroelastic Mode Distribution for Aircraft Wing Model in Subsonic Air Flow

2010 ◽  
Vol 2010 ◽  
pp. 1-23 ◽  
Author(s):  
Marianna A. Shubov ◽  
Stephen Wineberg ◽  
Robert Holt
Keyword(s):  
Boundary Value Problem ◽  
Numerical Investigation ◽  
Air Flow ◽  
Affirmative Answer ◽  
Positive Answer ◽  
Aircraft Wing ◽  
Aircraft Wings ◽  
Flutter Speed ◽  
Wing Model ◽  
Analytical Formulas

In this paper, the numerical results on two problems originated in aircraft wing modeling have been presented.The first problemis concerned with the approximation to the set of the aeroelastic modes, which are the eigenvalues of a certain boundary-value problem. The affirmative answer is given to the following question: can the leading asymptotical terms in the analytical formulas be used as reasonably accurate description of the aeroelastic modes? The positive answer means that these leading terms can be used by engineers for practical calculations.The second problemis concerned with the flutter phenomena in aircraft wings in a subsonic, incompressible, inviscid air flow. It has been shown numerically that there exists a pair of the aeroelastic modes whose behavior depends on a speed of an air flow. Namely, when the speed increases, the distance between the modes tends to zero, and at some speed that can be treated as the flutter speed these two modes merge into one double mode.

Analysis of Drag for an Aircraft Wing Model with and without Winglet

2011 ◽  
Vol 1 (7) ◽  
pp. 89-91
Author(s):  
Mitul Patel ◽  
◽  
Sharvil Shah ◽  
Dharmendra Dubey
Keyword(s):  
Aircraft Wing ◽  
Wing Model

Structural and Modal Analyses of Naca 66-206 Aircraft Wing Model

2019 ◽  
pp. 182-191
Author(s):  
Ismail Bogrekci ◽  
Pinar Demircioglu ◽  
H. Saygin Sucuoglu ◽  
Emrah Guven ◽  
Neslihan Demir ◽  
...  
Keyword(s):  
Aircraft Wing ◽  
Wing Model
Sign in / Sign up

Export Citation Format

Share Document