Searched for: subject%3A%22three%255C+dimensional%255C+flow%22
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document
Hoeijmakers, H.W.M. (author)
The physical aspects, the mathematical modeling, the development and application of computational methods for the simulation of vertical flows are described. The high-Reynolds number vortex flows considered are assumed to be steady, sub-critical and such that the structure of the flow is well-ordered and consists of thin shear layers and slender...
report 1989
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Hounjet, M.H.L. (author)
A description is given of the method CAR88 for the calculation of steady and time-linearized unsteady subsonic and supersonic flow about complex 2-D and 3-D configurations. The method belongs to the category of the socalled panel methods. Results of applications in supersonic flow are shown which have been made to a 2-D oscillating flat plate, a...
report 1988
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Velldman, A.E.P. (author), Lindhout, J.P.F. (author), de Boer, E. (author)
A description is given of VISIAN - a simulation method for 2-D viscous flows with strong viscous-inviscid interaction. The mathematical mode and the numerical algorithm are presented. VISIAN has been coupled with the inviscid-flow solver TRAPS. Results are shown for a number of airfoils; a comparison is made with results from other computations...
report 1988
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Labrujère, T.E. (author), Maarsingh, R.A. (author), Smith, J. (author)
Measurements on a simple aircraft model in both an appropriately sized and a relatively large, low-speed, solid-wall test section were used to analyse the accuracy and consistency of measured-boundary-condition (MBC) methods. For completeness, the classical method of images, with two different correction procedures, was also analysed. For the...
report 1988
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Boerstoel, J.W. (author)
An analysis of various alternative approaches in grid generation is presented. A grid-generation procedure for complex aircraft configurations could be based on a combination of three subprocesses, . decomposition of the flow domain into about 100 hexahedronal blocks, . trilineair transfinite interpolation to generate initial grid point...
report 1986
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Hoeijmakers, H.W.M. (author)
In part I of this report a method is described for computing the incompressible flow about slender, thin wings with leading-edge vortex separation. It is assumed that both the wing and the flow field are symmetric with respect to the x—z plane. The method can handle delta—like wings of quite general planform and shape. However, in the...
report 1986
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Koppenol, P.J. (author)
A computational method for solving the 3D Euler equations is studied. The method is based upon an upwind flux-difference splitting scheme by Osher, exhibiting an implicit mechanism for numerical viscosity, in connection with an explicit time-marching finite-volume technique. The computer program is developed to run efficiently on both a scalar...
report 1985
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Labrujere, T.E. (author)
A description is given of a method for the determination of global corrections for wall interference in both solid- and ventilated wall windtunnels, 2D as well as 3D. The method is based on the assumption that the flow velocity is known at a control surface surrounding the model and that the main part of the flow field may be considered...
report 1984
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Smith, J. (author)
The applicability of two-dimensional flexible solid wall test sections for three-dimensional testing is theoretically investigated for linearized subsonic flow. The method uses known interference velocity distributions along a targer line (derived from a method of images for this particular study). From these, wall shapes are calculated that...
report 1984
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Lindhout, J.P.F. (author), van den Berg, B. (author), Elsenaar, A. (author)
At the workshop nine participants presented the results of their calculations for a practical test case. The test case deals with the 3D turbulent boundary layer development, including separation, on the root section of a swept wing. The employed calculation methods comprise 3D integral methods as well as field methods. A short description of...
report 1981
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Joosen, C.J.J. (author), Sytsma, H.A. (author)
With the purpose of evaluating the adequacy of the NLR Panel Method with respect to the prediction of the flow around 3-D configurations with mechanical high-lift devices, potential flow calculations have been carried out for a swept-wing/body combination with part-span flaps at low speed. Several configurations as well as several calculation...
report 1979
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Tijdeman, H. (author)
Based on experimental observations an illustration is given of typical effects occiirring in high subsonic and transonic flow around oscillating airfoils and wings. It is shown that in this speed regime the unsteady airloads are influenced considerably by the interaction of the steady and unsteady flow fields. Moreover the periodical motion of...
report 1975
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