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 Bergsma, F. (author), Moerke, N. (author), Zaaijer, S. (author), Hoeijmakers, H.W.M. (author) conference paper 2013
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 van Loo, S. (author), van Terwisga, T.J.C. (author), Hoeijmakers, H.W.M. (author), Hoekstra, M. (author) conference paper 2012
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 Koop, A.H. (author), Hoeijmakers, H.W.M. (author), Schnerr, G.H. (author), Foeth, E.J. (author) conference paper 2006
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 Hoeijmakers, H.W.M. (author) public lecture 1993
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Hoeijmakers, H.W.M. (author)An analysis is presented of results of a computational method to simulate the steady compressible vortical type of flow around a 65deg sharpedged cropped delta wing. The discussion emphasizes some more fundamental aspects of the numerical simulation such as the separation of the flow, the structure of the leadingedge vortex core and the flow...report 1991
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 Hoeijmakers, H.W.M. (author) doctoral thesis 1989
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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 highReynolds number vortex flows considered are assumed to be steady, subcritical and such that the structure of the flow is wellordered and consists of thin shear layers and slender...report 1989
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Hoeijmakers, H.W.M. (author)A survey Is presented of several aspects of the use and further development of panel methods in aerodynamics. Aspects discussed include possible types of boundary conditions, low versus higherorder formulations, simulation of subsonic and supersonic flow and modeling of wakes as well as of leadingedge vortex separation. Also discussed are...report 1987
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de Bruin, A.C. (author), Hoeijmakers, H.W.M. (author)Laminar and turbulent boundary layer calculations were carried out on the leeward side of a flat sharpedged delta wing. The prediction of laminarturbulent boundary layer transition and the prediction of secondary separation are addressed in some detail.report 1986
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Hoeijmakers, H.W.M. (author)In this lecture methods are discussed for the numerical simulation of vortical type of flows. The various methods in use at present are discussed in some detail, primarily with a view towards threedimensional steady flow applications such as vortex wakes and leadingedge vortex flows. Some of the computational aspects of the numerical...report 1986
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Hoeijmakers, H.W.M. (author)Activities in the Netherlands in the area of simulating lowspeed flows using vortex elements are summarized. Aspects of some of the methods developed are highlighted and plans for future work are indicated.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 leadingedge 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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Hoeijmakers, H.W.M. (author), Verhaagen, N.G. (author)Modem aircraft configurations derive their highangleofattack capabilities to a large extent from the separation induced vortex flow from leading and side edges. In this paper theoretical and experimental investigations into vortex flow aerodynamios are described. Emphasis is placed on the description of the flow over slender highly swept wings...report 1985
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Hoeijmakers, H.W.M. (author)In this report an approximate method is described for computing, through the unsteady analogy, the shape of steady vortex wakes downstream of aircraft configurations in steady flight. In the analogy the steady fully threedimensional problem is reduced to a twodimensional timedependent problem, corresponding to the evolution of a two...report 1985
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Hoeijmakers, H.W.M. (author)In Part I if this report a method is described for approximately computing the shape of the steady vortex wake downstream of an aircraft configuration in steady flight through the unsteady analogy. In the analogy the steady fully threedimensional problem is reduced to a twodimensional timedependent problem, corresponding to the evolution of a...report 1985
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Hoeijmakers, H.W.M. (author), Rizzi, A. (author)The numerical solution for the inviscid incompressible flow about a 70deg swept delta wing at 20 deg incidence is considered. Two solutions are presented and compared in detail. The first solution is obtained employing a freevortexsheet panel method that solves for the potential flow with "fitted" vortical flow regions. This type of method is...report 1984
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Hoeijmakers, H.W.M. (author)A review is presented of computational methods to simulate the aerodynamics of configurations with leadingedge vortex flow. The various methods in use at present are discussed in some detail, primarily with a view towards threedimensional steady flow applications. The strengths and weaknesses of the methods are indicated and results of...report 1984
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Hoeijmakers, H.W.M. (author)This lecture discusses methods for the numerical solution of vortical type of flows about wings. The various methods are discussed primarily with a view toward threedimensional subsonic steady flow applications. The lecture is meant to give some insight into the weakness, strengths and prospects of the different methods. The various methods in...report 1983
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Hoeijmakers, H.W.M. (author)A review is presented of computational methods for the determination of the characteristics of vortical type flows occurring in aircraft aerodynamics. The review covers primarily computational methods for computing the downstream development of vortex wakes and methods for computing the characteristics of configurations with leadingedge and...report 1983
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Hoeijmakers, H.W.M. (author)A panel method (NLRAERO) is described for the computation of the velocity and pressure distribution of complex configurations in linearized subsonic and supersonic flow. The configurations that can be dealt with may consist of any number of slender and pointed bodylike components and any number of thin and mildly cambered lifting components. It...report 1982
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