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Jentink, H.W. (author)
This report concerns the application of laser anemometry for flight testing and other aircraft-related measurements. The laser anemometry technique and previous work in this field are reviewed and applications are described. A comparison of possibilities of laser anemometry with conventional techniques shows some unique advantages of laser...
report 1990
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den Boer, R.G. (author)
An experimental investigation revealed that the d5mamic response of a given pressure tube depends not only on the mean local pressure and the frequency, but also on the pressure amplitude and the boundary-layer at the tube entrance. By analyzing the flow at the entrance of the tube, the parameters are determined, which possibly play a role in...
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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van den Berg, J.I. (author)
In the development of mathematical simulation methods for engineering processes, it is essential to validate the mathematical models. Its results must be compared with results from other calculation methods or measurements. This is especially true in computational fluid dynamics (CFD). It is essential that an engineer developing mathematical...
report 1987
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Oskam, B. (author), van den Berg, B. (author)
The symposium demonstrated the importance of research in the area of mechanical high-lift systems for transport aircraft to improve the total performance of current transports. Computational techniques are shown to provide new tools for high-lift design. With regard to drag reduction by laminar flow control it is concluded that the information...
report 1985
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de Bruin, A.C. (author)
The three dimensional flow field around delta wings with leading-edge vortex flow can be computed with panel methods. However, secondary flow separation may occur on the leeward surface of the wing. The associated free vortex sheet can be modeled in the potential flow calculation method, if the location of the secondary separation is provided by...
report 1983
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Rienstra, S.W. (author)
A study is made of sound propagation through axially varying ducts with mean flow. Several analytical and numerical approaches are considered, and discussed with respect to their possibilities and limitations. Two new analytical theories, relevant for low and for high frequencies, are worked out in some detail. A fortuitously available *)...
report 1983
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Vogelaar, H.L.J. (author)
A description is given of the two-dimensional test setup in the pressurized wind tunnel HST of the NLR, for the testing of multiple airfoils at high Reynolds numbers. Results of the first tests with this setup are validated. For this validation a number of additional tests were performed in the HST as well as in the atmospheric wind tunnel HST 3...
report 1983
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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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van der Vooren, J. (author), van der Kolk, J.T. (author), Slooff, J.W. (author)
A description will be presented of a computer program system that is being used for the prediction of aircraft steady aerodynamic characteristics. Properties of the system are described from two different viewpoints. One is that of the aerodynamic designer, who needs an information system to predict lift, moment and drag characteristics and to...
report 1982
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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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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
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Kubota, H. (author)
Three-dimensional glancing-shock/turbulent boundary-layer interaction has been investigated at the Cranfield Institute of Technology in two separate test programmes using a 2.5 x 2.5 inch intermittent tunnel and a 9 x 9 inch inch continuous tunnel, at a Mach number of approximately 2.5. The experimental results include oil-flow pictures, vapour...
report 1980
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Pot, P.J. (author)
Extensive measurements of mean and fluctuating quantities in a 2-D wake shed from a flat plate and in the flow field of a 2-D wake merging into a boundary layer are described. The 'results are given in tabular and graphical form.
report 1979
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van den Berg, B. (author)
An experiment is described on a wing flap configuration, which was so designed that nowhere flow separations occur, apart from a small laminar separation bubble on the wing nose. The measurements comprise surface-pressure measurements, boundary layer and wake traverses, and surface-flow visualizations. Three angles of attack have been applied...
report 1979
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Kooi, J.W. (author)
An experiment is described in which a nominal normal shock impinges on a turbulent flat plate boundary layer. The wall pressure distribution in the interaction region was measured for Mach numbers in front of the shock of 1.40, 1.44 and 1.46. The Reynolds number based on shock position was 18 X 10(6) and based on momentum thickness at the start...
report 1978
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van der Assem, D. (author), Daniels, D.H.W. (author)
report 1977
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Dickman, C.C. (author)
Starting in 1946 as the College of Aeronautics, the Cranfield Institute of Technology was granted university status in 1969. In 1993 it changed its name to Cranfield University.
report 1977
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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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