H.-J. Steiner, M. Hornung, S. Baur, F. Holzapfel

A framework of methods for calculating aerodynamic forces and moments of aircraft configurations with strong propeller-wing coupling is presented and applied for a UAV with a large number of control inputs. A nonlinear lifting-line method is used for the calculation of lifting surface aerodynamics. By the use of nonlinear two-dimensional airfoil data the method yields good results even at angles of attack beyond stall. Blade element theory combined with momentum theory and Goldstein?s assumption is used to calculate the propeller forces and moments as well as the induced flow field in the propeller slipstream. Lifting surface and propeller aerodynamics are coupled in an iterative way to model the mutual influence on each other. The induced velocity of bodies of revolution is modeled based on slender body theory and superimposed on the free stream to yield the influence on lifting surfaces and propellers. The methods are used to calculate the aerodynamic dataset for a simulation model of a UAV with strong propeller-wing coupling and a large number of control inputs. An approach is presented for identifying the interdependence of flight states and control inputs to allow for an optimized design of computational experiments. The goal of this optimization process is to generate an aerodynamic dataset containing as much information about the system as possible with a given limited number of computations.

Deutscher Luft- und Raumfahrtkongress 2010

Conference Paper

englisch

21,0 x 29,7 cm, 11 Seiten

Deutscher Luft- und Raumfahrtkongress Tagungsband - Manuskripte, 2010, 2010, ; S.461-471; 2010; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

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2010