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Aerodynamic shape optimisation of a proprotor and its validation by means of CFD and experiments

Published online by Cambridge University Press:  27 January 2016

G. Droandi  and
G. Gibertini
G. Droandi*
Affiliation:
Dipartimento di Scienze e Tecnologie Aerospaziali, Politecnico di Milano, Milano, Italy
G. Gibertini
Affiliation:
Dipartimento di Scienze e Tecnologie Aerospaziali, Politecnico di Milano, Milano, Italy
*
giovanni.droandi@polimi.it
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Abstract

The aerodynamic shape design of a proprotor for a tiltrotor aircraft is a very complex and demanding task because it has to combine good hovering capabilities with high propeller efficiency. The aim of the present work is to describe a two-level procedure and its results for the aerodynamic shape design of a new rotor blade for a high-performance tiltwing tiltrotor aircraft taking into account the most important flight conditions in which the aircraft can operate. Span-wise distributions of twist, chord and aerofoil were chosen making use of a multi-objective genetic optimiser that worked on three objectives simultaneously. A non-linear sweep angle distribution along the blade was designed to reduce the power losses due to compressibility effects during axial flight at high speed. During the optimisation process, the aerodynamic performance of the blade was evaluated with a classical two-dimensional strip theory solver. The optimised blade was than analysed by means of a compressible Navier-Stokes solver and calculations were validated comparing numerical results with experimental data obtained from wind-tunnel tests of a scaled model of the proprotor.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 119 , Issue 1220 , October 2015 , pp. 1223 - 1251
Copyright
Copyright © Royal Aeronautical Society 2015

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