On the vortex flow over delta and double-delta wings

An experimental and theoretical investigation is described of the flow above and downstream of a 76° delta wing and two double-delta wings (sweep 76°/60° and 76°/40°, respectively, kink at 50 % chord). The flow pattern is visualized employing a laser-light-sheet technique. For the case of the delta wing experimental results are compared with...

A higher order panel method applied to Vortex sheet roll-up

The paper describes a computational method for two-dimensional vortex sheet motion in incompressible flow. The procedure utilizes a second-order panel method, an adaptive panel scheme and a concept for treating highly rolled-up portions of the vortex sheet. Results are presented for the roll-up of the wake behind an elliptically loaded wing, a...

A Higher-order panel method for the computation of the flow about slender delta wings with leading-edge vortex separation

For the limiting cases of conical flow about delta wings and time dependent 2-D development of the wake behind the trailing edge of wings a new second-order panel method is described. It is demonstrated that the panel method is stable for the mixed design/analysis boundary conditions characterizing both problems. The method for following 2-D...

Aspects of second- and third-order panel methods demonstrated for the two-dimensional flat plate problem

Characteristics of three second-order and two third-order panel method formulations for the incompressible flow about a flat plate at incidence are investigated. The second order methods employ quadratic representations for the doublet distribution, either based on quadratic B-splines or on a combination of a Taylor series expansion and finite...

A panel method for the determination of the aerodynamic characteristics of complex configurations in linearized subsonic or supersonic flow. Part 3. Description of computer code NLRAERO

A panel method has been developed for the computation of the velocity and pressure distribution and the aerodynamic characteristics of complex configurations in linearized subsonic or supersonic flow. A computer code has been developed to perform the calculations. The configuration may consist of any number of bodies as fuselage, tiptanks, pods,...

A panel method for the determination of the aerodynamic characteristics of complex configurations in linearized subsonic or supersonic flow. Part 1. Description and application

A detailed description is given of the theory underlying a panel method (NLRAERO) for the computation of the velocity and pressure distribution, load distributions, forces and moments on complex configurations in linearized subsonic or supersonic flow. The method can be considered as an improved and extended version of Woodward's method USSAERO....

A panel method for the determination of the aerodynamic characteristics of complex configurations in linearized subsonic or supersonic flow. Part 2. Evaluation of aerodynamic influence coefficients

A panel method for the computation of the velocity and pressure distribution on complex configurations in subsonic or supersonic flow has been described in Part I of the present report. This part of the report describes the evaluation of the aerodynamic influence coefficients. Expressions are derived for the (near-field) influence coefficients...

A computational model for the calculation of the flow about wings with loading-edge vortices