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Windtunnel investigation with a two-dimensional airfoil on the effect of blowing over a flap and over a control surface

van den Berg, B. (author)

The first part of the investigation deals with blowing over a flap deflected to angles up to 75°. The width of the blowing slot, located in the wing just ahead of the flap, could be varied. Lift, drag and pitching moment have been measured. The results have been compared with those of other similar eiperiments. In the second part the effect of...

report 1962

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Windtunnel investigation on the effect of blowing over the flap and over the wing nose at various aspect ratios sweep angles and flap spans

van den Berg, B. (author)

Part. I. Text, tables, fig. 1-5 Part. II. Fig. 6-63 (flap blowing results) Part. III. Fig. 64-103 (nose blowing results)

report 1965

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Enige beschouwingen over de kwaliteit van de stroming op de meetplaats van de LST 8x6 : Deel II : enige begrippen uit de statistische turbulentietheorie en de toepassing ervan op de berekening van de uitdemping en van de werking van gazen en van contractie

de Vries, O. (author), van den Berg, B. (author)

Concept rapport

report 1967

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Reynolds number and Mach number effects on the maximum lift and the stalling characteristics of wings at low speeds

van den Berg, B. (author)

A literature study has been made of the effect of Reynolds number variations on the stall of wings. It appeared that large changes in maximum lift and type of stall may occur up to very high Reynolds numbers. The nature of these changes varies essentially for airfoils of different thickness and for moderately and highly swept wings. The Mach...

report 1969

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Some notes on two-dimensional high-lift tests in wind tunnels

van den Berg, B. (author)

Lecture in AGARD-VKI lecture series on "Assessment of lift augmentation devices", 20-24 April, 1970

report 1970

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Voorstel voor een nieuwe lage-snelheid windtunnel voorzien van een meetplaats van 8x6 m. Deelrapport 2: Aerodynamische aspecten van het circuit

van den Berg, B. (author)

report 1970

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Voorstel voor een meetopstelling voor drie-dimensionaal grenslaagonderzoek in de LST 3x2

van den Berg, B. (author)

report 1970

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Measurements in a three-dimensional incompressible turbulent boundary layer in an adverse pressure gradient under infinite swept wing conditions

van den Berg, B. (author), Elsenaar, A. (author)

On a wind tunnel model, especially designed to check calculation methods, measurements were made of a three-dimensional turbulent boundary layer under infinite swept wing conditions in an adverse pressure gradient, with a three-dimensional separation near the trailing edge. Accurate measurements of the external flow field, the mean velocity...

report 1972

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The law of the wall in two- and three- dimensional turbulent boundary layers

van den Berg, B. (author)

The law of the wall has been extended to three-dimensional flows, The effects of both the pressure gradient and the inertial forces have been considered. The deduced wall law is valid when the deviations from the simple two-dimensional law of the wall are small. Agreement with measurements is found within the possible experimental error.

report 1973

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Measurements in an incompressible three-dimensional turbulent boundary layer under infinite swept wing conditions and a comparison with theory

van den Berg, B. (author), Elsenaar, A. (author), Lindhout, J.P.F. (author), Wesseling, P. (author)

First a three-dimensional turbulent boundary-layer experiment is described. This experiment has been carried out with the specific aim to provide a test-case for calculation methods. Much attention has been paid to the design of the test set-up. An infinite swept wing flow has been simulated with good accuracy. The initially two-dimensional...

report 1974

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A three-dimensional law of the wall for turbulent shear flows

van den Berg, B. (author)

An extended law of the wall is derived for three-dimensional flows. This law of the wall describes the variation of the magnitude and the direction of the velocity close to the wall. The effects of both the pressure gradient and the inertial forces have been taken into account. The derived wall law is valid only when the deviations from the...

report 1974

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Three-dimensional separation of an incompressible turbulent boundary layer on an infinite swept wing

Elsenaar, A. (author), van den Berg, B. (author), Lindhout, J.P.F. (author)

An experiment is described in which a three-dimensional boundary layer flow under infinite swept wing conditions is simulated. A description is given of the development of the boundary layer in a region of an adverse pressure gradient leading to increased cross flows and finally terminating in a three-dimensional. separation. Measurements are...

report 1975

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Calculation of the flow around a swept wing, taking into account the effect of the three-dimensional boundary layer. Part I: Wing with turbulent boundary layer

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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Investigations of three-dimensional incompressible turbulent boundary layers

van den Berg, B. (author)

A theoretical study is made of the flow near the wall in a three-dimensional turbulent boundary layer. An extended law of the wall is derived, which predicts the variation of the magnitude and direction of the velocity close to the wall. Furthermore an experimental investigation is described. Measurements were performed in a three-dimensional...

report 1976

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Calculation of the flow around a swept wing, taking into account the effect of the three-dimensional boundary layer. Part II: Wing with laminar boundary layer on the lower surface

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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European research programme on viscous flows : Eurovisc Annual Report

van den Berg, B. (author), Cousteix, J. (author), Fanneløp, T.K. (author), Hirschel, E.H. (author), Smith, P.D. (author)

report 1978

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Tweede interimrapport over "Het inbouwen van viskeuze effecten in de panelenmethode voor profielen met kleppen"

Oskam, B. (author), van den Berg, B. (author)

report 1978

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Boudary layer measurements on a two-dimensional wing with flap

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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A method for the calculation of 3D boundary layers on practical wing configurations

Lindhout, J.P.F. (author), Moek, G. (author), de Boer, E. (author), van den Berg, B. (author)

This paper gives a description of a calculation method for 3D turbulent and laminar boundary layers on non-developable surfaces. A simple eddy viscosity model is incorporated in the method. Special attention is given to the organization of the computations to circumvent as much as possible stepsize limitations. The method is also able to proceed...

report 1979

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Boundary layer measurements on a two-dimensional wing with flap and a comparison with calculations

van den Berg, B. (author), Oskam, B. (author)

Measurements were performed on a wing flap configuration, which was so designed that flow separations occur nowhere, apart from a small laminar separation bubble on the wing nose. The measurements comprise surface pressure measurements, boundary layer and wake traverses at 16 stations, and flow visualization tests to establish the presence of...

report 1979