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Wind-tunnel tests of the ERICA tiltrotor optimised air-intake

Published online by Cambridge University Press:  01 March 2018

G. Gibertini ,
A. Zanotti ,
G. Campanardi ,
F. Auteri ,
D. Zagaglia  and
G. Crosta
G. Gibertini*
Affiliation:
Dipartimento di Scienze e Tecnologie Aerospaziali, Politecnico di Milano, Campus Bovisa, Via La Masa 34, 20156 Milano, Italy
A. Zanotti
Affiliation:
Dipartimento di Scienze e Tecnologie Aerospaziali, Politecnico di Milano, Campus Bovisa, Via La Masa 34, 20156 Milano, Italy
G. Campanardi
Affiliation:
Dipartimento di Scienze e Tecnologie Aerospaziali, Politecnico di Milano, Campus Bovisa, Via La Masa 34, 20156 Milano, Italy
F. Auteri
Affiliation:
Dipartimento di Scienze e Tecnologie Aerospaziali, Politecnico di Milano, Campus Bovisa, Via La Masa 34, 20156 Milano, Italy
D. Zagaglia
Affiliation:
Dipartimento di Scienze e Tecnologie Aerospaziali, Politecnico di Milano, Campus Bovisa, Via La Masa 34, 20156 Milano, Italy
G. Crosta
Affiliation:
Leonardo Helicopters, HSD Department, via G.Agusta 520, Cascina Costa di Samarate (VA), Italy
*
giuseppe.gibertini@polimi.it
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Abstract

Wind-tunnel tests were carried out to evaluate the performance of the Computational Fluid Dynamics (CFD)-based air-intake duct shape optimisation of the European platform tiltrotor ERICA. A 1/2.5 scale model including the nacelle, the external portion of the wing and two interchangeable internal ducts reproducing the baseline and optimised shape were manufactered to be tested in the large wind tunnel of Politecnico di Milano. Moreover, tests were carried out with the model equipped with rotating blade stubs. The comprehensive experimental campaign included tests reproducing different forward flight conditions of the aircraft including cruise and conversion phases. The evaluation of the internal duct performance was carried out by measuring total pressure losses and flow distortion by directional probes at the Aerodynamic Interface Plane (AIP). Additional pressure measurements were carried out on the internal surface of the duct to compare the pressure distributions along the air-intake. The experimental results confirmed that the optimised duct offers significantly improved performance with respect to the baseline configuration not only in cruise, representing the flight condition considered for the CFD optimisation, but also for the conversion condition. In particular, a remarkable reduction of the total pressure drop at the AIP was found with the optimised duct with the only exception for the stubs-on configuration in cruise. Indeed, the present investigation highlighted that the design of the blade stubs, particularly their length, represents a very critical aspect for air-intake performance tests due to significant disturbances that could be induced by the stubs’ wake on the internal duct flow.

Keywords

AerodynamicsWind TunnelAir-IntakeTiltrotor
Type
Research Article
Information
The Aeronautical Journal , Volume 122 , Issue 1251 , May 2018 , pp. 821 - 837
Copyright
Copyright © Royal Aeronautical Society 2018 

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References

REFERENCES

1. Pahlke, K. and Demaret, B. ONERA and DLR contributions to improve environmental friendliness of rotorcraft, AHS International 73rd Annual Forum & Technology Display, 9-11 May 2017, Fort Worth, Texas, US.Google Scholar
2. Seddon, J. and Goldsmith, E.L. Intake Aerodynamics, AIAA Education Series, 1985, New York, NY, US.Google Scholar
3. Jeracki, R.J. and Heinze, W. Prop-fan data support study, Technical report CR-152141, 1978, NASA.Google Scholar
4. Atalayer, C., Friedrichs, J. and Wulff, D. S-Duct intake configuration sensitivity of a highly loaded turboprop by CFD methods, ASME Turbo Expo 2015: Turbine Technical Conference and Exposition, 15-19 June 2015, Montreal, Canada.Google Scholar
5. Saha, K., Singh, S.N. and Seshadri, V. Computational analysis on flow through transition S-diffusers: Effect of inlet shape, J Aircr, 2007, 44, (1), pp 187-193.Google Scholar
6. Alli, P., Nannoni, F. and Cicalé, M. ERICA: the European tilt-rotor design and critical technology projects, AIAA 2003-2515, AIAA International Air and Space Symposium and Exposition: The Next 100 Years, 14-17 July 2003, Dayton, Ohio, US.Google Scholar
7. Garavello, A., Benini, E., Ponza, R., Scandroglio, A. and Saporiti, A. Aerodynamic optimization of the ERICA tilt-rotor intake and exhaust system, 37th European Rotorcraft Forum, 13-15 September 2011, Ticino Park, Italy.Google Scholar
8. Gibertini, G., Auteri, F., Campanardi, G., Macchi, C., Zanotti, A. and Stabellini, A. Wind-tunnel tests of a tilt-rotor aircraft, Aeronautical J, 2011, 115, (1167), pp 315-322.Google Scholar
9. Gibertini, G., Zanotti, A., Droandi, G., Grassi, D., Campanardi, G., Auteri, F., Aceti, A. and Le Pape, A. Wind-tunnel tests of a heavy-class helicopter optimised for drag reduction, Aeronautical J, 2016, 120, (1231), pp 1446-1467.Google Scholar
10. Bryer, D.W. and Pankhurst, R.C. Pressure-Probe Methods for Determining Wind Speed and Flow Direction, National Physical Laboratory, London, 1971.Google Scholar
11. Zanotti, A. Test conclusion report, Technical report TETRA/WP3/D3.3, 2017.Google Scholar
12. Gibertini, G. Wind tunnel test data analysis, Technical report TETRA/WP4/D4.1, 2017.Google Scholar