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Rotorcraft Aerodynamics and Aeroacoustics

Objective

To generate a basis for quiet and efficient future helicopters. To this end, such tools as code development, feasibility study and experiments are applied.

For validation of the codes featuring now higher prediction performances, wind tunnel tests will be performed with a modern, more complex model rotor again equipped with pressure sensors. A further goal of the wind tunnel tests is to investigate direct noise reduction measures such as low tip speeds and noise oriented flight procedures. For analysing the feasibility of quiet helicopter designs, a dedicated study is conducted.

The activities related to the different tasks are summarized in the following:

Euler and Navier-Stokes Codes:

Prediction methods of unsteady transonic pressure distribution, shocks, wave drag, viscous drag and boundary layer characteristics are improved. The flight condition addressed is mainly hover.

Full Potential Code:

A common prediction model and a validated and documented computer code for transsonic pressure distribution for supplying rotor performances and loads is established.

Boundary Element Methods

Free wake generating codes for prediction of blade pressure distribution particularly for flight conditions with interactions between rotor wake and rotor blades as in descent and flare and for transonic flow conditions are improved.

Quiet Helicopter Study

Chances and risks of future Quiet Helicopter development are studied and the related requirements are defined.

Parametric Wind Tunnel Tests

Wind tunnel tests with a Mach-scaled rotor equipped with pressure transducers and advanced, exchangeable blade tips for code validation and study of noise reduction measures of modern complex rotors will be performed in the DNW.

Aeroacoustic Codes

Aeroacoustic codes addressing high speed and broad band noise are improved and validated, the first by different approaches such as unsteady Euler, acoustic analogy and Kirchoff integral formulation in order to identify the most capable method.

Funding Scheme

CSC - Cost-sharing contracts

Coordinator

EUROCOPTER DEUTSCHLAND GMBH
Address
Industriestrasse 4
Donauworth
Germany

Participants (15)

Agusta SpA
Italy
Address
Via Giovanni Agusta 520
21017 Cascina Costa Di Samarate Varese
CENTRO ITALIANO RICERCHE AEROSPAZIALI SCPA
Italy
Address
Via Maiorise
81043 Capua
Eurocopter France SARL
France
Address
Etablissement De Marignane
13725 Marignane
GERMAN - DUTCH WIND TUNNEL
Netherlands
Address
31,Voorsterweg 31
8316 PR Marknesse
GERMAN AEROSPACE CENTRE
Germany
Address
Lilienthalplatz 7
38108 Braunschweig
INSTITUTO SUPERIOR TECNICO
Portugal
Address
1,Avenida Rovisco Pais 1
1049-001 Lisboa
Institute of Computational Engineering Alfapi SA
Greece
Address
304,Messoghion
15500 Athens
Office National d'Études et de Recherches Aérospatiales (ONERA)
France
Address
29 Avenue De La Division Leclerc
92322 Châtillon
POLYTECHNIC OF MILAN
Italy
Address
Piazza Leonardo Da Vinci 32
20133 Milano
STICHTING NATIONAAL LUCHT- EN RUIMTEVAARTLABORATORIUM
Netherlands
Address
Anthony Fokkerweg 2
1006 Amsterdam
Secretary of State for Defence - Ministry of Defence
United Kingdom
Address
Ively Road
GU14 0LX Farnborough - Hampshire
The Engineering Academy of Denmark
Denmark
Address
1,Anker Engelundsvej
2800 Lyngby
UNIVERSITAET STUTTGART
Germany
Address
21,Pfaffenwaldring 21
70585 Stuttgart
UNIVERSITY OF BRISTOL
United Kingdom
Address
University Walk, Queens Building
BS8 1TR Bristol, Clifton
WESTLAND HELICOPTERS LTD.
United Kingdom
Address
Lysander Road
Yeovil, Somerset