Searched for: subject%3A%22Swept%255C%2Bwings%22
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Handojo, V.H. (author), Meddaikar, M.Y. (author), Dillinger, J.K.S. (author), Sodja, J. (author), De Breuker, R. (author)
This paper presents a semi-experimental method which can be used to predict the gust response of a wind tunnel model. The method incorporates transfer functions of the wind tunnel model – in this case a flexible forward swept wing – which are obtained using sweep excitations with a gust generator. The prediction results are then compared with...
conference paper 2019
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Groot, K.J. (author)
Laminar-turbulent transition dictates an increase in skin friction. The resulting turbulent skin friction contributes to approximately 40% of the total drag of commercial aircraft. Reducing the turbulent flow region by postponing transition can therefore significantly reduce the carbon footprint and costs of flying. Transition prediction is...
doctoral thesis 2018
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Serpieri, J. (author), Kotsonis, M. (author)
In this study, experiments are performed towards the identification and measurement of unsteady modes occurring in a transitional swept wing boundary layer. These modes are generated by the interaction between the primary stationary and travelling cross-flow instabilities or by secondary instability mechanisms of the stationary cross-flow...
journal article 2018
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Serpieri, J. (author)
The research presented in this booklet focusses on the cross-flow instability. Applying traditional and advanced flow diagnostics, the boundary layer evolution is studied in detail. The topology and evolution of both primary and secondary instability mechanisms is revealed with unprecedented detail for experimental research paving the way for...
doctoral thesis 2018
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Veldman, A.E.P. (author), Lindhout, J.P.F. (author)
An outline is presented of a new code, called VISIAN, for the analysis of aerodynamic flows with strong viscous-inviscid interaction. The code is based on the recently developed quasi-simultsuieous method for the calculation of strongly interacting boundary layers. The feasibility of this method has already been demonstrated liy means of a...
report 1983
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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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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
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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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van den Berg, B. (author), Piers, W.J. (author), de Boer, E. (author)
The attached flow around a swept wing has been calcTilated with allowance for the effects of boundary layer and wake. In part I a swept wing was considered with a turbulent boundary layer on both the upper and lower wing surface. The present part of the study deals with the calculation of the flow around the same swept wing with a laminar...
report 1977
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Lindhout, J.P.F. (author), de Boer, E. (author)
This report consists of two parts. The first part describes a finite-difference scheme for the computation of 3D laminar boundary layers over developable surfaces. The stability of the first variation of the difference scheme is investigated. Some results of actual boundary-layer calculations are presented for flows over swept wings. The second...
report 1976
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Lindhout, J.P.F. (author), de Boer, E. (author)
A method is presented to compute the 3D compressible turbulent boundary layer on an adiabatic wall under infinite swept wing conditions. The mathematical model of turbulence is based on a generalisation of Bradshaw's 2D shear stress equation. This results in a system of 5 equations valid along 5 distinct characteristics. A brief discussion is...
report 1975
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Piers, W.J. (author), Schipholt, G.J. (author), van den Berg, B. (author)
The attached flow around a swept wing has been calculated with allowance for the effects of boundary layer and wake. The outer potential flow has been computed with an adapted version of the NLR panel method. The displacement effect of the boundary layer and the wake has been taken into account by the outflow concept. For the calculation of the...
report 1975
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Van-Den-Berg, B. (author), Elsenaar, A. (author), Lindhout, J.P.F. (author), Wesseling, P. (author)
journal article 1975
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Elsenaar, A. (author), Boelsma, S.H. (author)
On a wind tunnel model measurements have been made of the six components of the Reynolds stress tensor in a three-dimensional incompressible turbulent boundary layer under infinite swept wing conditions in an adverse pressure gradient, with a three-dimensional separation near the trailing edge. These measurements complement the mean velocity...
report 1974
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