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Improved experimental and theoretical tools for helicopter aeromechanic and aeroacoustic interactions


Objectives and content:
The main industrial objectives of the proposed project is to assure and improve safety, public acceptance and economic/technical efficiency of current and future helicopters. For this reason, the proposed research activities are targeted to avoid technical problems from the beginning of development of anew helicopter or to overcome problems appearing during flight-testing in short time.

In order to be able to do so, the following targets have to be attained:- Acquisition of knowledge about specific interference and coupling phenomena, - Validation of existing wind tunnel test methodology and its extension to higher complexity, - Verification and extension of existing comprehensive theoretical models, - Definition of design criteria and know-how about the technical potential of future helicopters.

In order to effectively perform the envisaged investigations, the participants will take advantage of different European wind tunnels and helicopter models, particularly suited for the different problems.

These may be characterised in the following:- Effects due to low speed interference:
- vehicle pitch up during transition from hover to forward speed, (task 3.1with generic rotor/fuselage model in 24ft DRA wind tunnel);
- control problems by main/tail rotor interaction during quartering flight(task 3.2 with generic main/tail rotor model in 24 ft DRA wind tunnel);
- control problems and extreme bank angles during sideward flight (task3.3 with B0105 model [with main/tail rotor] in DNW);
- Effects appearing over larger areas of the helicopter flight envelope:
- tail shake (by interference between hub/pylon wake and tail planes),(task 4.1 with DAUPHIN model [with main rotor] in ONERA S2 wind tunnel);
- tail rotor noise (heavily influenced by the main rotor wake) (task 4.2 with model of task 3.3 in DNW);
- stability (described by dynamic derivatives of the rotor) (task 4.3 with generic main rotor model in ONERA S1 wind tunnel).The acquired methods and know-how will be applied immediately to support and improve the design of new rotors, helicopters and derivatives and to alleviate problems of flying helicopters.

Call for proposal

Data not available


Eurocopter Deutschland GmbH

81663 München

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EU contribution
€ 0,00

Participants (11)