Finite Element Analysis of Transonic Flows Over Thin Airfoils PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Finite Element Analysis of Transonic Flows Over Thin Airfoils PDF full book. Access full book title Finite Element Analysis of Transonic Flows Over Thin Airfoils by S. T. K. Chan. Download full books in PDF and EPUB format.
Author: S. T. K. Chan Publisher: ISBN: Category : Languages : en Pages : 69
Book Description
A finite element algorithm is described for computing steady and unsteady (oscillatory and transient) transonic flows over thin airfoils by solving directly the unsteady, nonlinear transonic potential equation based on small disturbance theory. The numerical algorithm is developed using the concept of finite elements in conjunction with the least squares method of weighted residuals applied to both space and time. The basic element presently used is a product of an element in space and an element in time. The former has a cubic expansion inside each element, while the latter is a quadratic Lagrange element. The embedded shocks are smeared and, in computing flow over lifting airfoils, use is made of the far field asymptotic solution to increase computational efficiency. For each time step, the finite element discretization in both space and time results in a recurrence relationship in the form of a banded system of algebraic equations, which is solved by Gaussian eliminations. Sample problems of steady flow over lifting airfoils and unsteady flow over airfoils executing harmonic motion are calculated to demonstrate the applicability and validity of the present approach. The solution procedures are found to be adequately accurate and very efficient, with unsteady solution obtainable in less than ten minutes CPU time on a CDC 6600 computer. (Author).
Author: S. T. K. Chan Publisher: ISBN: Category : Languages : en Pages : 69
Book Description
A finite element algorithm is described for computing steady and unsteady (oscillatory and transient) transonic flows over thin airfoils by solving directly the unsteady, nonlinear transonic potential equation based on small disturbance theory. The numerical algorithm is developed using the concept of finite elements in conjunction with the least squares method of weighted residuals applied to both space and time. The basic element presently used is a product of an element in space and an element in time. The former has a cubic expansion inside each element, while the latter is a quadratic Lagrange element. The embedded shocks are smeared and, in computing flow over lifting airfoils, use is made of the far field asymptotic solution to increase computational efficiency. For each time step, the finite element discretization in both space and time results in a recurrence relationship in the form of a banded system of algebraic equations, which is solved by Gaussian eliminations. Sample problems of steady flow over lifting airfoils and unsteady flow over airfoils executing harmonic motion are calculated to demonstrate the applicability and validity of the present approach. The solution procedures are found to be adequately accurate and very efficient, with unsteady solution obtainable in less than ten minutes CPU time on a CDC 6600 computer. (Author).
Author: H. C. Chen Publisher: ISBN: Category : Languages : en Pages : 112
Book Description
A finite element program is described for computing steady and unsteady (oscillatory and transient) transonic flows over thin airfoils by solving directly the unsteady, nonlinear transonic potential equation based on small disturbance theory. The present numerical algorithm is developed using the concept of finite elements in conjunction with the least squares method of weighted residuals applied to both space and time. The basic element presently used is a product of an element in space and an element in time. The former has a cubic expansion inside each element, while the latter is a quadratic Lagrangian element. For each time step, the finite element discretization in both space and time results in a recurrence relationship in the form of a banded system of algebraic equations, which is solved by Gaussian elimination. The embedded shocks are smeared and a matching scheme for computing effectively flow over lifting airfoils is also incorporated in the program. The present computer program is composed of two parts: the first part (designated as UTRANL-I) generates, from a limited number of input cards, the necessary mesh information and, if desired, produces a CALCOMP mesh plot; the second part (UTRANL-II) carries out the analysis and displays the pressure coefficients along the chordline on printer plots. Two sample cases of flow over a NACA 64A 410 and a NACA 64A 006 airfoils are given to demonstrate the applicability and usage of the program. Te solution procedures are found to be quite efficient and accurate, permitting the aerodynamic forces to be calculated to engineering accuracy in less than ten minutes CPU time on a CDC 6600 computer for the most time consuming case among all those studied. (Author).
Author: S. T. K. Chan Publisher: ISBN: Category : Languages : en Pages : 99
Book Description
A finite element program is described for the analysis of subsonic and transonic flows over thin airfoils by solving the nonlinear transonic potential equation based on small disturbance theory. The present numerical algorithm uses the concept of finite elements in conjunction with the least square method of weighted residuals. Since the governing equation is of the elliptic-hyperbolic type, a 'one-sided assembly technique' was devised and adapted in the supersonic region to restore the directional property of the flow, which was removed by the exclusion of entropy from the transonic potential equation. The finite element discretization results in a system of banded nonlinear algebraic equations, which is solved by direct iterations. The elements presently used include triangles and quadrilaterals with the perturbed potential function and velocity components as nodal unknowns. Boundary conditions of both Dirichlet and Neumann types are therefore imposed conveniently. Secondary unknowns are computed directly without resorting to numerical differentiation. The computer program is separated into two parts: the first part (designated as STRANL-I) generates the necessary mesh information and, if desired, produces a mesh plot and optimal nodal numbering as well; STRANL-II carries out the analysis and displays the pressure coefficients along the chord line on printer plots. Two sample cases of flow over a NACA 64 A006 and a 6% thick circular arc are given.
Author: Dennis L. Hunt Publisher: ISBN: Category : Languages : en Pages : 93
Book Description
Two finite element upwind techniques were investigated to see if convergent solutions could be obtained from the transonic potential equation for steady flow over thin airfoils. The first technique involves the use of parabolic upwind functions, that when added to the shape functions weight the upstream node in the supersonic region more than the downwind nodes. The second technique integrates the finite element equations over the area that influences the solution (i.e., the area inside a mach cone). (Author).
Author: S. T. K. Chan Publisher: ISBN: Category : Aerodynamics, Transonic Languages : en Pages : 112
Book Description
The finite element technique is applied to steady incompressible, subsonic and transonic flow with the end objective being the analysis of unsteady transonic flow. A triangular cubic element is used and the Galerkin method of weighted residuals is adapted to control the error. The formulation is based on the small disturbance but nonlinear transonic equation for inviscid compressible flow. Full potential formulations with small disturbance assumptions are also investigated. The governing equations are cast into the Poisson type for which finite element analogs are constructed, and the solution is then obtained by iterative procedures. Boundary conditions involving the normal derivative of the unknown functions are conveniently cast into boundary integrals and added to the right-hand side of the equations. In the case where more than two unknown parameters are related, such as those along the branch cut, Lagrangian multipliers are used to introduce these constraints and a special equation solver is developed for these computations. Techniques are developed for analyzing lifting flow under free flight conditions with general provisions for surface tangency, wake and far field boundary conditions. This generality allows for computation of combinations of internal axd external flow (as an airfoil in a wind tunnel), as well as free flight, about arbitrary geometry. Unsteady transonic flow calculations are also presented for a NACA 64 A006 with an oscillating 25% chord control surface.
Author: James E. Marsh Publisher: ISBN: Category : Aerodynamic load Languages : en Pages : 186
Book Description
The finite element method was used to solve the nonlinear, small-disturbance, transonic, velocity-potential equation for problems of steady flow over a circular cylinder and over a thin-airfoil in a uniform steady airstream. The governing differential equation is valid for inviscid, irrotational, isentropic flow of a perfect gas to include weak shocks providing airflow separation does not occur. For compressible subsonic and transonic flows the nonlinear small-disturbance equations was expressed in iterative form as a sequence of linear equations which was solved iteratively until the difference between two successive solutions became arbitrarily small. For analysis purposes the infinite flowfield was replaced by a finite but sufficiently large domain that was discretized with sector elements for the cylinder problem and rectangular elements for the airfoil problem. The finite element equtions were obtained from Galerkin's Method of Weighted Residuals. Boundary conditions of the Neumann type were imposed along the surface contour of the cylinder and along an approximate boundary in accordance with classical thin-airfoil theory for the airfoil. For both problems Dirichlet conditions were imposed along the farfield boundary from an asymptotic solution which satisfies the actual infinity condition and is valid in the farfield.
Author: S. T. K. Chan
Author: S. T. K. Chan
Author: H. C. Chen
Author: S. T. K. Chan
Author: Dennis L. Hunt (2LT, USAF.)
Author: Dennis L. Hunt
Author: S. T. K. Chan
Author: S. T. K. Chan
Author: James E. Marsh
Author: 
Author: S. T. K. Chan