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HELICOPTER ROTOR/FUSELAGE INTERACTIONAL AERODINAMICS

Objective

The aim of this project is to produce a computer model capable of predicting the interactional aerodynamic effects between helicopter rotor blades and the fuselage.
The general scope of the program was the improvement of methodologies and prediction methods for interactional aerodynamics, in order to provide benefits in the helicopter design phase.

The computational methods available to predict isolated helicopter main rotor flow, isolated fuselage flow and rotor/fuselage interaction phenomena were discussed.

The experimental activities to generate new data covered a wide spectrum to meet the needs of the code validation process. The tests included:
isolated rotor (subscale) in hover and forward flight;
fuselage alone;
rotor/fuselage (subscale) in hover and forward flight;
rotor/fuselage (subscale) in forward flight.

Isolated and uncoupled rotor calculations were performed. The different methods used covered a wide range of theoretical approaches, from the simplest momentum theory to the boundary element method with a free wake rotor calculations. The correlations showed that at least a lifting line method with a vortex rotor wake is necessary to simulate correctly the velocity field above the rotor disk.

Isolated and uncoupled fuselage calculations were performed using methods. Correlations with the experiment were satisfactory.

The combined rotor/fuselage calculation methods typically use a lifting line representation for the rotor with a prescribed wake model and a steady panel method for the fuselage. The calculated results obtained show relatively good agreement with the experiment above the rotor disk for the mean and instantaneous velocities.

A global rotorcraft model based on the boundary element method has been formulated and preliminary results have been presented. A panel method representation of the fuselage and of the thick blades isused along with a prescribed rotor wake model. The modelling tools developed in the project need to be improved in order to increase the range of configurations for which they provide reliable calculations.
It will commence with a survey to identify and compare the computational methods currently available to European industry and research centres.

Experimental campaigns will be carried out using 3 different wind-tunnel test facilities. The test matrix and the most significant measurements for each campaign will be specified, such as the measurements required for CFD purposes.

The complete rotor/fuselage interactional aerodynamics problem will be outlined, from the computational point of view, by addressing some intermediate topics: firstly, the isolated rotor and fuselage analysis will be considered; secondly, the uncoupled rotor and fuselage case (the flowfield of the former analysis taking into account the presence of the latter, and vice versa); thirdly, the coupled rotor/fuselage case (combining rotor and fuselage flowfield calculations); and finally, global integrated models. For each topic, the following aspects will be covered: the methods and the algorithms to be assessed, using selected test cases from the updated experimental database; the improvements/enhancements needed for each method and algorithm; and the possible development of new computational models.

The final report will provide a specification for the future development of an overall helicopter prediction methodology which will model the interactional aerodynamics effects on the performance of the aircraft.

Fields of science

Programme(s)

Topic(s)

Data not available

Call for proposal

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Funding Scheme

CSC - Cost-sharing contracts

Coordinator

Agusta SpA
EU contribution
No data
Address
Via Giovanni Agusta 520
21017 Cascina Costa di Samarate Varese
Italy

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Total cost
No data

Participants (12)

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Last update: 18 November 1992

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Permalink: https://cordis.europa.eu/project/id/AERO0011

European Union, 2024