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Solution of inverse problem for a flow around an airfoil
Šimák, Jan ; Feistauer, Miloslav (advisor) ; Felcman, Jiří (referee) ; Sváček, Petr (referee)
Title: Solution of inverse problem for a flow around an airfoil Author: Mgr. Jan Šimák Department: Department of Numerical Mathematics Supervisor: prof. RNDr. Miloslav Feistauer, DrSc., dr. h. c., Department of Numerical Mathematics Abstract: The method described in this thesis deals with a solution of an inverse problem for a flow around an airfoil. It can be used to design an airfoil shape according to a specified velocity or pressure distribution along the chord line. The method is based on searching for a fixed point of an operator, which combines an approximate inverse and direct operator. The approximate inverse operator, derived on the basis of the thin airfoil theory, assigns a corresponding shape to the specified distribution. The resulting shape is then constructed using the mean camber line and thickness function. The direct operator determines the pressure or velocity distribution on the airfoil surface. We can apply a fast, simplified model of potential flow solved using the Fredholm integral equation, or a slower but more accurate model of RANS equations with a k-omega turbulence model. The method is intended for a subsonic flow.
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Solution of inverse problem for a flow around an airfoil
Šimák, Jan ; Feistauer, Miloslav (advisor) ; Felcman, Jiří (referee) ; Sváček, Petr (referee)
Title: Solution of inverse problem for a flow around an airfoil Author: Mgr. Jan Šimák Department: Department of Numerical Mathematics Supervisor: prof. RNDr. Miloslav Feistauer, DrSc., dr. h. c., Department of Numerical Mathematics Abstract: The method described in this thesis deals with a solution of an inverse problem for a flow around an airfoil. It can be used to design an airfoil shape according to a specified velocity or pressure distribution along the chord line. The method is based on searching for a fixed point of an operator, which combines an approximate inverse and direct operator. The approximate inverse operator, derived on the basis of the thin airfoil theory, assigns a corresponding shape to the specified distribution. The resulting shape is then constructed using the mean camber line and thickness function. The direct operator determines the pressure or velocity distribution on the airfoil surface. We can apply a fast, simplified model of potential flow solved using the Fredholm integral equation, or a slower but more accurate model of RANS equations with a k-omega turbulence model. The method is intended for a subsonic flow.
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Finite volume method development for solution of 2D viscous fluid flow
Zúňiga, G. ; Maršík, František ; Kozel, Karel
A two-dimensional Finite Volume Method for solving the stationary incompressible non-dimensionalized Navier-Stokes equations is developed and employed to investigate the velocity and pressure fields in a non-orthogonal grid configuration. The method is tested on NACA0012 and Double Arc Airfoils. Numerical results are compared with the experiments of IT CAS for velocity and law Reynolds number (Re = 400) to the agreement rather good.
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