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Author: Yung-Huai Kuo Publisher: ISBN: Category : Aerodynamics, Transonic Languages : en Pages : 54
Book Description
The problem of constructing solutions for transonic flow over symmetric airfoils is treated for simplification of the mapping of the incompressible flow is emphasized. In the case of a symmetric Joukowski airfoil without circulation the mapping is relatively simple, but the coefficients in the power series are difficult to evaluate. As a means of simplification an approximate flow is used which differs only slightly from the exact incompressible one when the thickness is small. Flow with circulation is also considered by the same method.
Author: Yung-Huai Kuo Publisher: ISBN: Category : Aerodynamics, Transonic Languages : en Pages : 54
Book Description
The problem of constructing solutions for transonic flow over symmetric airfoils is treated for simplification of the mapping of the incompressible flow is emphasized. In the case of a symmetric Joukowski airfoil without circulation the mapping is relatively simple, but the coefficients in the power series are difficult to evaluate. As a means of simplification an approximate flow is used which differs only slightly from the exact incompressible one when the thickness is small. Flow with circulation is also considered by the same method.
Author: Publisher: ISBN: Category : Languages : en Pages :
Book Description
With the aim of developing a fast and accurate computer code for predicting the aerodynamic forces needed for a flutter analysis, some basic concepts in computational transonics are reviewed. The unsteady transonic flow past airfoils in rigid body motion is adequately described by the potential flow equation as long as the boundary layer remains attached. The two dimensional unsteady transonic potential flow equation in quasilinear form with first order radiation boundary conditions is solved by an alternating direction implicit scheme in an airfoil attached sheared parabolic coordinate system. Numerical experiments show that the scheme is very stable and is able to resolve the higher nonlinear transonic effects for filter analysis within the context of an inviscid theory.
Author: I-Chung Chang Publisher: ISBN: Category : Aerodynamics, Transonic Languages : en Pages : 211
Book Description
With the aim of developing a fast and accurate computer code for predicting the aerodynamic forces needed for a flutter analysis we review some basic concepts in computational transonics. The unsteady transonic flow past airfoils in rigid body motion is adequately described by the potential flow equation as long as the boundary layer remains attached. The two dimensional unsteady transonic potential flow equation in quasilinear form with first order radiation boundary conditions is solved by an alternating direction implicit scheme in an airfoil attached sheared parabolic coordinate system. Numerical experiments show that the scheme is very stable and is able to resolve the highly nonlinear transonic effects for flutter analysis within the context of an inviscid theory. (Author).
Author: Frank A. Dvorak Publisher: ISBN: Category : Languages : en Pages : 41
Book Description
A calculation method for transonic separated flow about two-dimensional airfoils at incidence is presented in this report. The method is capable of predicting the effects of both leading- and trailing-edge separated flows, although the former is usually associated with a complete collapse of the airfoil flow field, in which case the flow is no longer supercritical. A viscous potential flow iteration procedure provides the connection between potential flow, boundary layer and wake modules. The separated wake is modelled in the potential flow analysis by thin sheets across which exists a jump in velocity potential. These sheets are analogous to vorticity sheets in incompressible flow. The basic potential flow method is a modification of Jameson's full potential method. Calculations for four different airfoils have been compared with experiment for pressure distributions as well as integrated forces. The agreement between theory and experiment is generally good even when shock waves are present. (Author).
Author: J. A. Bennett Publisher: ISBN: Category : Aerodynamics Languages : en Pages : 376
Book Description
The report presents a method for describing the subsonic, viscid, attached flow about two-dimensional airfoils with applications to transonic flow. The method utilizes state-of-the-art technology to analyze all aspects of the flow and combines boundary layer solutions with inviscid pressure distribution prediction methods to obtain a 'complete' solution. This complete solution is represented by a pressure distribution at any point on the airfoil which relects the viscid, inviscid, and compressible effects in proper combination. The solution is programmed for an IBM7094 computer in which the required inputs are freestream flow conditions and airfoil geometry only. The program computes the pressure and boundary layer distribution using an iterative procedure to attain equilibrium conditions. These data, as well as the lift, drag and pitching moment of the viscid solution and the inviscid pressure distribution are provided as output. Methods for applying the results to analyze practical subsonic and transonic design problems are discussed. (Author).
Author: Yung-Huai Kuo
Author: Yung-Huai Kuo![Unsteady Transonic Flow Past Airfoils in Rigid-body Motion. [UFLO5]. PDF](https://books.google.com/books/content/images/frontcover/7wH8wQEACAAJ?fife=w80-h100)
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Author: I-Chung Chang
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Author: Karel Kozel
Author: Frank A. Dvorak
Author: James D. Sebastian
Author: B.M. Spee
Author: J. A. Bennett
Author: Ryuma Kawamura