A program for the computation of a compressible turbulent boundary layer under infinite swept wing conditions.

A method is presented to compute the 3D compressible turbulent boundary layer on an adiabatic wall under infinite swept wing conditions. The mathematical model of turbulence is based on a generalisation of Bradshaw's 2D shear stress equation. This results in a system of 5 equations valid along 5 distinct characteristics. A brief discussion is...

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...

An ALGOL-program for the calculation of incompressible three-dimensional turbulent boundary layers

A computer program has been prepared for the calculation of turbulent boundary layer development, based on a 3-D version of the turbulent energy method. The method is briefly discussed. The computer program is described in detail. The present program is restricted to developable surfaces.

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

Measurements of the Reynolds stress tensor in a three-dimensional turbulent boundary layer under infinite swept wing conditions

On a wind tunnel model measurements have been made of the six components of the Reynolds stress tensor in a three-dimensional incompressible turbulent boundary layer under infinite swept wing conditions in an adverse pressure gradient, with a three-dimensional separation near the trailing edge. These measurements complement the mean velocity...

Low speed windtunnel measurements on a two-dimensional flapped wing model using tunnel wall boundary layer control at the wing-wall junctions

An investigation on a two-dimensional wing model with a double-slotted trailing edge flap is described where tunnel wall boundeo'y layer control by blowing was applied to prevent premature flow separations at the junctions between the model and the tunnel walls. From the results it is concluded that tunnel wall boundary layer control at the wall...

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

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.

Memory Effect in a Turbulent Boundary-Layer Flow Due to a Relatively Strong Axial Variation of the Mean-Velocity Gradient

Measurements have been made of the distributions of mean velocity, turbulence intensities and turbulence shear-stress in a turbulent boundary-layer downstream of a hemi-spherical cap attached onto the plane rigid wall. The eddy-viscosity, when computed in the classical way according to Boussinesq's concept from the lateral gradient of the mean...

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

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...

Calculation of the displacement effect in two-dimensional subsonic attached flow around aerofoils: examples of calculations using measured displacement thicknesses

Using measured displacement thicknesses the classical displacement effect on lift and pressure distribution has been calculated for a number of aerofoils in viscous attached flow. For this purpose the displacement concept boundary condition (in its "leak flow" form) has been incorporated in a potential flow calculation method that uses a...

Contribution à la transition dans la couche limite

A l'aide de la méthode du ruban vibrant de Schubauer et Klebanoff. on a étudié expérimentalement l'évolution tridimensionnelle d'une perturbation sinusoïdale locale introduite dans une couche limite laminaire. Les distributions de la vitesse moyenne et de l'intensité de la composante axiale de la turbulence, de même que le spectre d'énergie de...