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Zandbergen, P.J. (author), van der Walle, F. (author)A survey is given of the results obtained at the NLR with respect to the determination of optimum body-ring wing configurations at zero lift. It is shown that if reliable data are required for practical shapes the use of exact flow theories is essential. The pressure distribution on the optimum configuration considered here is such that the...report 1962
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Zandbergen, P.J. (author), van der Walle, F. (author)A method is given for the calculation of the noise field of a propeller. This method is slightly different from that of Garrick and Watkins. It is believed that the differences in the results indicate the order of the inaccuracy due to the approximations inherent in the two methods. The noise field of two propellers is calculated to show these...report 1962
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Labrujere, Th.E. (author), Zandbergen, P.J. (author)The Coanda effect, being an expedient for the application of blowing boundary layer control^, has been investigated by the NLH to gain an insight into the basic principle and the laws by which it is governed, Within the framework of this investigation a potential theory is developed which, at any rate leads to a qualitative prediction of the...report 1963
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Maasdam, J. (author), Zandbergen, P.J. (author)This report gives a programme for the determination of the flow around a circular cone. Both the cases of zero-inclination and of a small inclination have been considered. The programme is written in the international machine language ALGOL and can therefore be operated on any computer having an ALGOL compiler. The purpose of this investigation...report 1963
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van der Walle, F. (author), Zandbergen, P.J. (author)This report presents a new method to find shapes that attain minimum wave drag under certain constraints. The constraints considered here are given values for the base area and the lift. The configuration is assumed to be embedded in a volume enclosed by two opposing circular Mach cones, one going through the most forward point of the...report 1964
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Zandbergen, P.J. (author)This report presents a method for the determination of axially-symmetric shapes with a given base area that are optimum with respect to wave drag in supersonic flow and which have finite nose angles. Use has been made of the exact non-linear differential equations for supersonic flow together with the shock equations. The computed results...report 1964
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van der Walle, F. (author), Raat, J. (author), Zandbergen, P.J. (author)In this report a method is presented to determine optimum shapes of bodies of revolution taking into account the shape dependent part of the base drag. The latter is achieved by using the Chapman assumption that the base pressure coefficient, when correlated with conditions at a suitable point near the base, depends only on the free-stream Mach...report 1964
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Baurdour, H.I. (author), Zandbergen, P.J. (author)In this report the drag-coefficient of an optimum body with a conical nose has been determined. The body was designed for a Mach number of the undisturbed stream equal to 3. It is found that the curve for the drag coefficient shows a definite kink at the design Mach number. The conclusion is reached that a more general approach for designing...report 1964
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Loeve, W. (author), Zandbergen, P.J. (author)In this paper, a discussion is given of some of the aerodynamic difficulties involved in the design of wings for high-subsonic speeds, and of the theoretical methods available to calculate sub-critical pressure distributions. It appears that until now only one of these methods, being in fact a semi-emperical one, is developed far enough to be of...report 1966
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Zandbergen, P.J. (author), Labrujere, Th.E. (author), Wouters, J.G. (author)The present report deals with the numerical treatment of the linearised lifting surface theory through a method which is based upon the representation of the pressure distribution on chordwise direction by a series of Chebyshew polynomials according to Laschka, and upon the determination of the spanwise integral involved by means of...report 1967
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Zandbergen, P.J. (author), Baurdoux, H.I. (author)The solution of sets of non-linear partial differential equations using the method of integral relations is considered. Emphasis is laid on the derivation of a general N-strip approximation algorithm. In order to check the applicability of this algorithm a program has been written to obtain the solution of the flow field around a circular cone...report 1968
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- Erdmann, S.F. (author), Zandbergen, P.J. (author) report 1969
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Labrujere, E. (author), Zandbergen, P.J. (author)Results are presented which are obtained by a new elaborate method developed at NLR for the determination of the characteristics of thin wings in subsonic flow. Attention is paid to the rate of convergence of the numerical solutions, especially with respect to the number of collocation points. Two rectangular wings have been treated in order to...report 1971
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Zandbergen, T. (author), de Boer, E. (author)A computer program written in Fortran IV and based on the method of Levinsky has been developed for the calculation of the spanwise lift distribution on wings with deflected slipstreams. This report gives a description of Levinsky's method and detailed information on the computer program. Results of computations are compared with experimental...report 1972
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- Zandbergen, T. (author), Joosen, C.J.J. (author) report 1974
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Zandbergen, T. (author), Maarsingh, R.A. (author), Joosen, C.J.J. (author)With the intent to test the qualities of the theoretical models used in two different calculation methods, pressure distributions have been measured on a simple half model wing-in-jet combination. The position of the jets relative to the wing was varied, mainly in a plane perpendicular to the span. Jet velocities of 1, 2 and 3 times the tunnel...report 1977
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Zandbergen, T. (author)The properties of a Helmholtz resonator type acoustic lining material may he seriously affected by intercellular water drain holes. This was shown by experiments in the NLR flow duct facility on an actual aircraft engine liner where drain holes caused a considerable shift in the frequency for maximum attenuation. Furthermore the drain holes...report 1979
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Zandbergen, T. (author), Maarsingh, R.A. (author)Based on comparison with results from special experiments, an evaluation has been performed of the method of Levinsky, Thommen, Yager and Holland, which is intended to calcxilate the spanwise lift distribution on wings immersed in propulsive jets. Various modifications of the original method have been investigated. It was found that the method,...report 1979
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Zandbergen, T. (author), Martlew, D.L. (author)The National Aerospace Laboratory NLR in the Netherlands and the National Gas Turbine Establishment NOTE operate similar acoustic flow duct facilities but with differences in their respective approaches to the measurement of attenuation and impedance of duct linings. A joint exercise was arranged with the object of comparing methods and results,...report 1981
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Zandbergen, T. (author)A three-microphone technique is presented for in-situ acoustic impedance measurements on double layer liners of the Helmholtz resonator type. It can be used under conditions of flow and arbitrary noise sources. The emphasis of this paper is the practical application of this technique, including microphone installation and the implications of...report 1981
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