Hostname: page-component-76fb5796d-wq484 Total loading time: 0 Render date: 2024-04-26T22:16:26.863Z Has data issue: false hasContentIssue false
  • English
  • Français

A parametric windtunnel test on rotorcraft aerodynamics and aeroacoustics (Helishape) — test procedures and representative results

Published online by Cambridge University Press:  04 July 2016

K.-J. Schultz ,
W. Splettstoesser ,
B. Junker ,
W. Wagner ,
E. Schoell ,
E. Mercker ,
K. Pengel ,
G. Arnaud  and
D. Fertis
K.-J. Schultz
Affiliation:
DLR, Braunschweig, Goettingen, Germany
W. Splettstoesser
Affiliation:
DLR, Braunschweig, Goettingen, Germany
B. Junker
Affiliation:
DLR, Braunschweig, Goettingen, Germany
W. Wagner
Affiliation:
DLR, Braunschweig, Goettingen, Germany
E. Schoell
Affiliation:
Eurocopter Deutschland, Ottobrunn, Germany
E. Mercker
Affiliation:
DNW, Emmeloord, The Netherlands
K. Pengel
Affiliation:
DNW, Emmeloord, The Netherlands
G. Arnaud
Affiliation:
Eurocopter France, Marignane, France
D. Fertis
Affiliation:
ALFAPI, Athens, Greece
Get access Rights & Permissions [Opens in a new window]

Abstract

Within the framework of a major European co-operative research project on rotorcraft aerodynamics and acoustics (Helishape), a parametric model rotor test was conducted in the open test section of the DNW using DLR's MWM test rig, and a highly instrumented model of a fully articulated ECF rotor equipped with blades of advanced design with two exchangeable blade tips. One set of blade tips (7A) was rectangular, while the other (7AD1) was a swept-back parabolic-anhedral shape. The objectives of this experimental research were to evaluate noise reduction techniques (conceptionally by variation of rotor speed, dedicated tip shapes and advanced aerofoils, as well as operationally, by identifying low noise, BVI-minimising, descent procedures) and to validate the partners’ aerodynamic and aeroacoustic codes. A comprehensive set of simultaneous acoustic and aerodynamic blade surface pressure data and blade dynamic and performance data was measured. In addition, valuable information on the tip-vortex geometry and blade-vortex miss distance was obtained by LLS flow visualisation. The experimental equipment, the test procedures, and the test matrix are briefly described. A survey of the main results is presented and the trends of the most important parameter variations for both rotors are discussed.

Type
Research Article
Information
The Aeronautical Journal , Volume 101 , Issue 1004 , April 1997 , pp. 143 - 154
Copyright
Copyright © Royal Aeronautical Society 1997 

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. Boxwell, D.A., Schmitz, F.H., Splettstoesser, W.R. and Schultz, K.-J. Model helicopter rotor high speed impulsive noise: measured acoustics and blade pressures, NASA TM 85850 and US-AAVRAD-COM TR-A-14, September 1983.Google Scholar
2. Splettstoesser, W.R., Schultz, K.-J., Boxwell, D.A. and Schmitz, F.H. Helicopter model rotor blade/vortex-interaction impulsive noise, scalibility and parametric variations, Proceedings 10th European Rotorcraft Forum, The Hague, August 1984 and NASA TM 86007, TM-84-A-7.Google Scholar
3. Zinner, R.A., Boxwell, D.A. and Spencer, R.H. Review and analysis of the DNW/Model 360 rotor acoustic database, 15th European Rotor-craft Forum, Amsterdam, September 1989.Google Scholar
4. Yu, Y.H., Landgrebe, A.J., Liu, S.R., Lorber, P.F., Jordan, D.E., Pollack, M.J. and Martin, R.M. Aerodynamic and acoustic test of a United Technologies model scale rotor at DNW, Proceedings, American Helicopter Society 46th Annual Forum, Washington DC, May 1990, pp 1233–1250.Google Scholar
5. Martin, R.M., Splettstoesser, W.R., Elliot, J.W. and Schultz, K.-J. Advancing side direction and retreating side interactions of model rotor blade-vortex interaction noise, NASA Technical Paper 2784 and AVSCOM Technical Report 87-B-3, 1988.Google Scholar
6. Schultz, K.-J. and Splettstoesser, W.R. Model tail rotor noise study in the DNW — measured acoustics, blade pressures, noise predictions, Paper No 78, Proceedings, 18th European Rotorcraft Forum, Avignon, September 1992.Google Scholar
7. Splettstoesser, W., Junker, B., Schultz, K.-J., Wagner, W., Weitemeyer, W., Protopsaltis, A. and Fertis, D. The Helinoise aero-acoustic rotor test in the DNW test documentation and representative results, DLR-Mitt. 93-09, 1993.Google Scholar
8. Seidel, M. and Maarsingh, R.A. Test capabilities of the German-Dutch Windtunnel DNW for rotors, helicopters and V/stol aircraft,Proceedings of the 5th European Rotorcraft and Powered Lift Aircraft Forum, September 1979.Google Scholar
9. Van Ditshuizen, J.C.A., Courage, G.D., Ross, R., and Schultz, K.-J. Acoustic capabilities of the German-Dutch Windtunnel (DNW), AIAA-83-0146, January 1983.Google Scholar
10. Stephan, M., Kloppel, V., and Langer, H.-J. A new windtunnel test rig for helicopter testing, Paper No 66, 14th European Rotorcraft Forum, September 1988.Google Scholar
11. Mercker, E., and Pengel, K. Flow visualisation of helicopter blade-tip vortices, Paper No 26, Proceedings 18th European Rotorcraft Forum, Avignon, September 1992.Google Scholar
12. Gelhaar, B., Junker, B. and Wagner, W. DLR-rotor test stand measures unsteady rotor aerodynamic data, Paper No C8, Proceedings 19th European Rotorcraft Forum, Cernobbio, Italy, September 1993.Google Scholar
13. Breustedt, W. (SCITRAN, transl) Data analysis on the rotor test stand program for interactive processing, NASA TM-77948, 1985.Google Scholar
14. Brooks, T.F., Jolly, R.J. and Marcolini, M.A. Determination of noise source contributions using scales model rotor acoustic data, NASA TP 2825, 1988.Google Scholar