Hostname: page-component-cd9895bd7-p9bg8 Total loading time: 0 Render date: 2024-12-28T22:28:54.749Z Has data issue: false hasContentIssue false

On the generation of a helicopter aerodynamic database

Published online by Cambridge University Press:  27 January 2016

M. Raffel*
Affiliation:
German Aerospace Center (DLR), Goettingen, Germany
F. De Gregorio
Affiliation:
Centro Italiano Ricerche Aerospaziali (CIRA), Capua, Italy
K. de Groot
Affiliation:
German Aerospace Center (DLR), Braunschweig, Germany
O. Schneider
Affiliation:
German Aerospace Center (DLR), Braunschweig, Germany
W. Sheng
Affiliation:
Department of Aerospace Engineering, University of Glasgow, UK
G. Gibertini
Affiliation:
Dipartimento di Ingegneria Aerospaziale, Politecnico di Milano, Italy
A. Seraudie
Affiliation:
Aerodynamics and Energetics Model Department, ONERA, Toulouse, France

Abstract

The GOAHEAD (Generation of an Advanced Helicopter Experimental Aerodynamic Database for CFD code validation) consortium was created in the frame of an EU-project in order to create an experimental database for the validation of 3D-CFD and comprehensive aeromechanics methods for the prediction of unsteady viscous flows. This included the rotor dynamics for complete helicopter configurations, i.e. main rotor – fuselage – tail rotor configurations with emphasis on viscous phenomena like flow separation and transition from laminar to turbulent flow. The wind tunnel experiments have been performed during two weeks in the DNW-LLF on a Mach-scaled model of a modern transport helicopter consisting of the main rotor, the fuselage, control surfaces and the tail rotor. For the sake of controlled boundary conditions for later CFD validation, a closed test section has been used. The measurement comprised global forces of the main rotor and the fuselage, steady and unsteady pressures, transition positions, stream lines, position of flow separation, velocity profiles at the test section inlet, velocity fields in the model wake, vortex trajectories and elastic deformations of the main and tail rotor blades.

Type
Research Article
Copyright
Copyright © Royal Aeronautical Society 2011

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1. Heineck, J.T., Yamauchi, G.K., Woodcock, A.J. and Lourenco, L. Application of three-component PIV to a hovering rotor wake, 2000. 56th annual forum of the American helicopter society, Virginia Beach, VA, USA.Google Scholar
2. Martin, P.B. and Leishmann, G.J. Trailing vortex measurements in the wake of a hovering rotor blade with various tip shapes, 2002. 58th annual forum of the American helicopter society, Montreal, Canada.Google Scholar
3. Raffel, M., Seelhorst, U. and Willert, C. Vortical flow structures at a helicopter rotor model measured by LDV and PIV, Aeronaut J, 1998, 102, (1012), pp 221227.Google Scholar
4. Murashige, A., Kobiki, N., Tsuchihashi, A., Nakamura, H., Inagaki, K. and Yamakawa, E. ATIC Aeroacoustic Model Rotor Test at DNW, 2000, 24th European rotorcraft forum, Marseille, France.Google Scholar
5. van der wall, B.G. and Richard, H. Analysis methodology for 3C-PIV data of rotary wing vortices, Experiments in Fluids, 2006, 40, pp 798812.CrossRefGoogle Scholar
6. Fey, U., De Groot, K. and Le Sant, Y. Thermography as a tool in wind tunnel testing, 2004, European Wind Tunnel Association (EWA), ANE3-CT-2004-502889, Network of Excellence, Priority 4, Aeronautics and space, Deliverable 2/10/2004.Google Scholar
7. Le Sant, Y., Marchand, M., Millan, P. and Fontaine, J. An overview of infrared thermography techniques used in large wind tunnels, Aerospace, Sci and Tech, 2002, 6, pp 355366.CrossRefGoogle Scholar
8. Quast, A. Detection of transition by infrared image technique, 1987, IEEE publication CH2449-7/87, ICIASF.Google Scholar
9. Jorgensen, F.E. Directional sensitivity of wire and fibre film probes, DISA Info, 1971, 11, pp 3137.Google Scholar
10. Chew, Y.T. and Ha, S.M. The directional sensitivities of crossed and triple hot-wire probes, J Phys E Sci Instrum, 1988, 21, pp 613620.Google Scholar
11. Lekakis, I.C. Adrian, R.J. and Jones, B.G. Measurement of velocity vector with orthogonal and non-orthogonal triple-sensor probes, Exp Fluids, 1989, 8, pp 228240.CrossRefGoogle Scholar
12. Durst, F., Noppenberger, S., Still, M. and Venzke, H. Influence of humidity on hot-wire measurements, Meas Sci Technol, 1996, 7, pp 15171528.CrossRefGoogle Scholar
13. Maciel, Y. and Gleyzes, C. Survey of multi-wire probe data processing techniques and efficient processing of four-wire probe velocity measurements in turbulent flows, Experiments in Fluids, 2000, 29, pp 6678.Google Scholar
14. Han, Y.O., George, W.K. and Hjarne, J. Effect of a contraction on turbulence. Part 1: Experiment, 2005, AIAA 2005-1119.Google Scholar
15. Sémézis, Y. and Beaumier, PH Determination de l’état de la couche limite sur des sections de pale d’helicoptère al’aide de films chauds, 1995, 31ème colloque 3AF, 2729 March 1995, Paris, France.Google Scholar
16. Séraudie, A., Perraud, J. and Moens, F. Transition measurement and analysis on a swept wing in high lift configuration, 2002, 23rd Congress of ICAS Toronto, 8-13 September 2002, Canada.Google Scholar
17. Perraud, J., Séraudie, A. and Moens, F. Transition on a high-lift swept wing in the European project EUROLIFT, J Aircr, September-October 2004, 41, (5).CrossRefGoogle Scholar
18. De Gregorio, F., Pengel, K. and Kindler, K. Industrial measurement campaign on fully equipped helicopter model, 2010, 15th Int Symposium on Applications of Laser Techniques to Fluid Mechanics, 7-10 July 2010, Lisbon, Portugal.Google Scholar
19. Pengel, K., Müller, R. and Van Der Wall, B.G. Stereo pattern recognition – the technique for reliable rotor blade deformation and twist measurements, 2002, AHS International Meeting on Advanced Rotorcraft Technology and Life Saving Activities, Utsunomiya, Tochigi, Japan.Google Scholar
20. Schneider, O. Analysis of SPR measurements from HART II, Aerospace Sci and Tech, 2005, 9, (5), pp 409420. Elsevier.Google Scholar
21. De Groot, K. Application of the infrared technology for investigations of the boundary layer, 2005, ONERA/DLR meeting MOTAR, Lille, France.Google Scholar
22. Schneider, O., van der wall, B.G. and Pengel, K. HART II blade motion measured by stereo pattern recognition (SPR), 2003, 59th Annual Forum of the American Helicopter Society, Phoenix, USA.Google Scholar
23. Schneider, O. and van der wall, B.G. Final analysis of HART II blade deflection measurement, 2003, 29th European Rotorcraft Forum, Friedrichshafen, Germany.Google Scholar