01 - Aircraft Design and Integrated Systems
VALIDATION OF AN AERODYNAMIC MODEL FOR THE ANALYSIS OF SUBSCALE TEST AIRCRAFT WITH DISTRIBUTED ELECTRICAL PROPULSION
O. Luderer¹, M. Jünemann¹, F. Thielecke¹; ¹Hamburg University of Technology, Germany
An aerodynamic model for the estimation of propeller-wing-interactions is implemented and validated with wind tunnel data. The integration into a subscale test aircraft design environment enables the consideration of the effects of distributed electrical propulsion systems at an early design stage. This allows aircraft designs with an optimized interaction between prop. system and elastic wings.