Computed hydrodynamic characteristics of various hull-keel configurations of a "Friendship 33". Special attention has been paid to the Winglet-Keel option of this yacht

Enige berekeningen met een panelmethode aan het zeiljacht ""Van de Stadt 29 - Sea-Dog"". Ontwerpnr. 267

Calculation of transonic flow by means of a shock-capturing field panel method

Two-dimensional tunnel wall interference for multi-element aerofoils in incompressible flow

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

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...

Evaluation of a method for the calculation of the pressure distribution on two-dimensional wing-flap configurations in subsonic flow (part II)

Evaluation of a method for the calculation of the pressure distribution on two-dimensional wing-flap configurations in subsonic flow (part I)

Potential flow calculations to support two-dimensional wind tunnel tests on high-lift devices

The applicability of potential flow calculations for developing high-lift devices, is evaluated by comparing calculated pressure distributions over wing sections with trailing and leading edge high-lift devices, and experimental results, obtained during routine wind tunnel tests.

The applicability of first and second order theory for the determination of subcritical pressure distributions on non-lifting aerofoils

Pressure distributions are calculated for a number of two-dimensional non-lifting symmetrical quasi-elliptical aerofoils with the uniformly valid first order theory and Gretler's second order theory. The results have been compared with exact solutions for incompressible and compressible subsonic flow. For non-elliptical nose shapes the results...