Searched for: subject%3A%22finite%255C+difference%255C+theory%22
(1 - 9 of 9)
document
Schippers, H. (author)
A description is given of TULIPS - a method for Transonic Unsteady Lifting Inviscid Potential-flow Simulation. The Mathematical formulation and the numerical approach are presented for flow about oscillating airfoils. TULIPS is based on the numerical integration of the unsteady full-potential equation in generalized coordinates. The equation is...
report 1988
document
Boerstoel, J.W. (author)
A survey of numerical methods for the calculation of inviscid Euler flows is presented. This survey has been prepared for AGAKD FDP WGOT: "Test cases for steady inviscid transonic or supersonic flows". The survey is augmented by a short assessment of the usefulness of the methods. For aerodynamic applications, the existing methods are in a...
report 1983
document
Boerstoel, J.W. (author)
The application of multigrid relaxation to transonic potential-flow calculation was investigated. Fully conservative potential flows around aerofoils were taken as test problems. The solution algorithm was based on Newton iteration. In each Newton iteration step, multigrid relaxation was used to calculate correction potentials. It was found that...
report 1981
document
Hoeijmakers, H.W.M. (author)
Characteristics of three second-order and two third-order panel method formulations for the incompressible flow about a flat plate at incidence are investigated. The second order methods employ quadratic representations for the doublet distribution, either based on quadratic B-splines or on a combination of a Taylor series expansion and finite...
report 1981
document
van der Vooren, J. (author), Huizing, G.H. (author), van Essen, A. (author)
A calculation method, based upon transonic small perturbation theory, is presented for the transonic flow about a semi-wing. The influence of a body can be simulated by prescribing appropriate transverse velocities in a vertical plane through the wing root. Due to the small perturbation assumption the wing should be thin and have little dihedral...
report 1981
document
Oskam, B. (author)
The viscous flow around multi-component airfoils has been calculated by solving incompressible potential flow and boxindary layer problems iteratively. The potential flow problem is solved by a revised version of the 2D NLR panel method. A model transport equation of turbulent stress is employed to calculate the turbulent boundary layer. The...
report 1980
document
van der Vooren, J. (author), Huizing, G.H. (author)
A method is discussed for the calculation of inviscid transonic flow about thin airfoils in moderately slow unsteady motion. It is an extension of a method which was developed by Ballhaus and Goorjian of NASA Ames and which is applicable for strictly slow unsteady motions only. The modifications involve extra unsteady terms in the boundary...
report 1980
document
Veldman, A.E.P. (author)
In this report a mathematical model is presented which can describe the dynamic behaviour of liquids in partially filled containers under low gravitational conditions. This model will be used for the evaluation of a series of experiments which the NLR has planned to be performed onboard Spacelab. Furthermore, the report contains a description of...
report 1979
document
van der Vooren, J. (author), Sanderse, A. (author)
A fully-conservative- finite difference algorithm is described to calculate the incompressible flow through a straight channel of varying rectangular cross section. Both the width and the height of the channel may vary independently. The algorithm has been used successfully in the design of the German-Dutch low speed wind tionel (DNW).
report 1977
Searched for: subject%3A%22finite%255C+difference%255C+theory%22
(1 - 9 of 9)