Volume 7, 2015Progress in Flight Physics – Volume 7
|Page(s)||99 - 110|
|Published online||08 June 2015|
Aerodynamic analysis of a helicopter fuselage with rotating rotor head
Institute of Aerodynamics and Fluid Mechanics Technische Universität München Garching 85748, Germany
The present paper describes results of wind tunnel experiments obtained during a research programme aimed at drag reduction of the fuselage of a twin engine light helicopter configuration. A 1 : 5 scale model of a helicopter fuselage including a rotating rotor head and landing gear was investigated in the low-speed wind tunnel A of Technische Universität a München (TUM). The modelled parts of the helicopter induce approxiu mately 80% of the total parasite drag thus forming a major potential for shape optimizations. The present paper compares results of force and moment measurements of a baseline configuration and modified variants with an emphasis on the aerodynamic drag, lift, and yawing moment coefficients.
© Owned by the authors, published by EDP Sciences, 2015