Hostname: page-component-cd9895bd7-gxg78 Total loading time: 0 Render date: 2024-12-22T09:55:55.931Z Has data issue: false hasContentIssue false
  • English
  • Français

Design of a rotor blade tip for the investigation of dynamic stall in the transonic wind-tunnel Göttingen

Published online by Cambridge University Press:  04 July 2016

B. Lütke ,
J. Nuhn ,
Y. Govers  and
M. Schmidt
B. Lütke*
Affiliation:
DLR, Department of Aeroelasticity, Göttingen, Germany
J. Nuhn
Affiliation:
DLR, Department of Aeroelasticity, Göttingen, Germany
Y. Govers
Affiliation:
DLR, Department of Aeroelasticity, Göttingen, Germany
M. Schmidt
Affiliation:
DLR, Systemhaus Technik, Brunswick, Germany
*
[email protected]
Get access Rights & Permissions [Opens in a new window]

Abstract

The aerodynamic and structural design of a pitching blade tip with a double-swept planform is presented. The authors demonstrate how high-fidelity finite element (FE) and computational fluid dynamic (CFD) simulations are successfully used in the design phase. Eigenfrequencies, deformation, and stress distributions are evaluated by means of a three-dimensional (3D) FE model. Unsteady Reynolds-averaged Navier-Stokes (RANS) simulations are compared to experimental data for a light dynamic stall case at Ma = 0.5, Re = 1.2 × 106. The results show a very good agreement as long as the flow stays attached. Tendencies for the span-wise location of separation are captured. As soon as separation sets in, discrepancies between experimental and numerical data are observed. The experimental data show that for light dynamic stall cases at Ma = 0.5, a factor of safety of FoS = 2.0 is sufficient if the presented simulation methods are used.

Keywords

Structural and aerodynamic designdynamic stallhelicopterdouble-swept rotor blade tiptransonic wind-tunnelexperimentCFDFEM
Type
Research Article
Information
The Aeronautical Journal , Volume 120 , Issue 1232 , October 2016 , pp. 1509 - 1533
Copyright
Copyright © Royal Aeronautical Society 2016 

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

REFERENCES

1. Liiva, J. Unsteady aerodynamic and stall effects on helicopter rotor blade airfoil sections, J Aircraft, 1969, 6, (1), pp 46–51.Google Scholar
2. Gardner, A.D., Richter, K., Mai, H., Altmikus, A.R.M., Klein, A. and Rohardt, C.-H. Experimental investigation of dynamic stall performance for the EDI-M109 and EDI-M112 airfoils, J American Helicopter Society, 2013, 58, (1), pp 1–13.Google Scholar
3. Le Pape, A., Pailhas, G., David, F. and Deluc, J.M. Extensive wind tunnel tests measurements of dynamic stall phenomenon for the OA209 airfoil including 3D effects, Proceedings of the 33rd European Rotorcraft Forum, Kazan, Russia, 11-13 Sepember 2007, 1, pp 320-335.Google Scholar
4. Merz, C.B., Wolf, C.C., Richter, K., Kaufmann, K. and Raffel, M. Experimental investigation of dynamic stall on a pitching rotor blade tip, STAB Symposium, München, Germany, 2014.Google Scholar
5. McCroskey, W.J. and Fisher, R. Dynamic stall of airfoils and helicopter rotors, AGARD, 1972, (R595).Google Scholar
6. Mulleners, K., Kindler, K. and Raffel, M. Dynamic stall on a fully equipped helicopter model, Aerospace Science and Technology, 2012, 19, (1), pp 72–76.CrossRefGoogle Scholar
7. Schultz, K. J., Splettstoesser, W., Junker, B., Wagner, W., Schoell, E., Mercker, E., Pengel, K., Arnaud, G. and Fertis, D. A parametric windtunnel test on rotorcraft aerodynamics and aeroacoustics (Helishape): Test procedures and representative results, Aeronautical J, 1997, 101, (1004), pp 143–154.Google Scholar
8. Rauch, P., Gervais, M., Cranga, P., Baud, A., Hirsch, J.-F., Walter, A. and Beaumier, P. Blue edge: The design, development and testing of a new blade concept, 67th Annual Forum of the American Helicopter Society Proceedings, May 2011, Virginia Beach, Virginia, US.Google Scholar
9. Scott, M., Sigl, D. and Strawn, R. Computational and experimental evaluation of helicopter rotor tips for high speed forward flight, J Aircraft, 1991, 28, (6), pp 403–409.Google Scholar
10. Yeager, W.T. Jr, Noonan, K.W., Singleton, J.D., Wilbur, M.L. and Mirick, P.H. Performance and vibratory loads data from a wind-tunnel test of a model helicopter main-rotor blade with a paddle-type tip, Tech. rep., NASA TM-4754, 1997.CrossRefGoogle Scholar
11. Brocklehurst, A. and Barakos, G.N. A review of helicopter rotor blade tip shapes, Progress in Aerospace Sciences, 2013, 56, pp 35–74.CrossRefGoogle Scholar
12. Mullins, B.R., Smith, D.E., Rath, C.B. and Thomas, S.L. Helicopter rotor tip shapes for reduced blade vortex interaction - an experimental investigation part II, 34th AIAA Aerospace Sciences Meeting and Exhibits, 1995, 96, (0149)CrossRefGoogle Scholar
13. Wiggen, S. and Voss, G. Development of a wind tunnel experiment for vortex dominated flow at a pitching lambda wing, CEAS Aeronautical J, 2014, pp 1–10.Google Scholar
14. Schimke, D., Link, S. and Schneider, S. Noise and performance improved rotor blade for a helicopter, European Patent, (EP 2 505 500 A1), March 2011.Google Scholar
15. Schewe, G. Force and moment measurements in aerodynamics and aeroelasticity using piezoelectric transducers, Springer Handbook of Experimental Fluid Mechanics, 2007, 96, pp 596–616.Google Scholar
16. Bailie, J.A., Ley, R.P. and Pasricha, A. A summary and review of composite laminate design guidelines, Final Report, NASA Contract NAS1-19347, October 1997, Langley RC, Hampton.Google Scholar
17. ANSYS, Inc. ANSYS Mechanical APDL Theory Reference, Release 14.5., October 2012, SAS IP, Inc.Google Scholar
18. Allemang, Randall J. and Brown, D.L. A correlation coefficient for modal vector analysis, Proceedings of the 1st International Modal Analysis Conference, Orlando, Florida, US 1982, 1, pp 110-116.Google Scholar
19. Lütke, B., Schmidt, M., Sinske, J. and Neumann, J. Structural design of an instrumented double-swept wind tunnel model, Proceedings of the 20th Conference on Composite Materials, 2015, Copenhagen.Google Scholar
20. Neumann, J. and Krüger, W. Coupling strategies for large industrial models, Computational Flight Testing , edited by Kroll, N., Radespiel, R., van der Burg, J.W. and Sorensen, K., Notes on Numerical Fluid Mechanics and Multidisciplinary Design, Springer, 2013, 123, pp 207–222.Google Scholar
21. Puck, A. and Schürmann, H. Failure analysis of FRP laminates by Mmeans of physically based phenomenological models, Composites Science and Technology, 1998, 58, (7), pp 1045–1067.Google Scholar
22. Gerhold, T., Friedrich, O., Evans, J. and Galle, M. Calculation of complex three-dimensional configurations employing the DLR-TAU-Code, AIAA-paper, (167), 1997.Google Scholar
23. Menter, F.R. Zonal two equation k − ω turbulence models for aerodynamic flows, AIAA 24th Fluid Dynamics Conference, (2906), 1993, Orlando, Florida, US.CrossRefGoogle Scholar
24. Gerhold, T. and Neumann, J. The Parallel Mesh Deformation of the DLR TAU-Code, New Results in Numerical and Experimental Fluid Mechanics VI, Springer Berlin Heidelberg, 2008, pp 162–169.CrossRefGoogle Scholar
25. Gardner, A.D., Richter, K. and Rosemann, H. Prediction of the wind tunnel sidewall effect for the iGREEN wing-tailplane interference experiment, New Results in Numerical and Experimental Fluid Mechanics VII, Springer Berlin Heidelberg, 2010, pp 75–82.Google Scholar