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1: Introduction

The program FLZ-Vortex is used to examine the distribution of forces and momenta of complex airplane constructions. The airplane construction is set up by means of a 3D-editor.
For computations the Vortex-Lattice-Method VLM is applied.
In contrast to E. Truckenbrodt's wing panel method VLM has the ability to integrate the dihedral of a wing into the computation. The simpler lifting-line and wing panel methods could only analyse flat wings.
As with the aforementioned methods VLM uses the airfoil's mean camber line for computation. At first airfoil thickness and viscous influence (skin-friction) are not taken into account.

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