ARSPNS: a method to calculate steady and unsteady potential flow about fixed and rotating lifting and nonlifting bodies

A new method ARNSPNS is described for the calculation of steady and time-linearized unsteady incompressible potential flow about arbitrary lifting and nonlifting bodies in an arbitrary mean steady flow field, including rotation. The method belongs to the category of the so-called panel methods. Applications have been made to wind turbines...

Two-dimensional modelling of capillary liquid flow in a thin annulus

One of the experiments performed on board Spacelab, involves a partially filled annular cylinder which is subjected to prescribed motions (Ref. 1). The interest in this configuration arises from its practical use; for instance, the coolant in IRAS was stored in an annulus-like tank. In this report, a mathematical model for the transient liquid...

A system for computer aided analysis and design of multi-element airfoils

A program system has been developed as a tool for interactive analysis and design of multi-element airfoils in incompressible viscous flow. A global description of the system is given. It involves the application of three computational methods, one for the analysis of viscous flow and one for the analysis of inviscid flow around multi-element...

Evaluation of Thing's method for the calculation of the lift discription on a wing in propulsive jets

The calculation method presented by Ting, Liu and Kleinstein in reference 3 has been subjected to an evaluation study, principally on the basis of experimental data obtained from special experiments on a half wing immersed in two jets. Very satisfactory results were found for the unflapped wing lying centrally within the jets. Both flap...

Finite difference calculation of incompressible flow through a straight channel of varying rectangular cross section, with application to low speed wind tunnels

A fully-conservative- finite difference algorithm is described to calculate the incompressible flow through a straight channel of varying rectangular cross section. Both the width and the height of the channel may vary independently. The algorithm has been used successfully in the design of the German-Dutch low speed wind tionel (DNW).

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

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...

A simple finite-difference technique for the computation of three-dimensional incompressible laminar boundary layers. Part I: Description of the method

This report consists of two parts. The first part describes a finite-difference scheme for the computation of 3D laminar boundary layers over developable surfaces. The stability of the first variation of the difference scheme is investigated. Some results of actual boundary-layer calculations are presented for flows over swept wings. The second...

Airfoil design by the method of singularities via parametric optimization of a geometrically constrained least squares object function

The present report describes a method for the design of airfoils in incompressible flow which, subject to geometrical constraints generate approximately a given distribution of the pressure coefficient along the projection of the airfoil chord on an axis parallel to the onset flow. The flow is simulated by means of a distribution of...

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...