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

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...

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

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...

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

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...

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.

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...

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

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

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

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

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

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...

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

Concept rapport

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

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

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

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...