Hostname: page-component-78c5997874-mlc7c Total loading time: 0 Render date: 2024-11-14T22:47:28.946Z Has data issue: false hasContentIssue false
  • English
  • Français

Integration of high bypass ratio engines on modern transonic wings for regional aircraft

Published online by Cambridge University Press:  04 July 2016

E. Greff ,
K. Becker ,
M. Karwin  and
S. Rill
E. Greff
Affiliation:
Deutsche Airbus, Bremen
K. Becker
Affiliation:
Deutsche Airbus, Bremen
M. Karwin
Affiliation:
Deutsche Airbus, Bremen
S. Rill
Affiliation:
Deutsche Airbus, Bremen
Get access Rights & Permissions [Opens in a new window]

Abstract

Changing airline scenarios and aggravated congestion have led to an increasing demand for new regional aircraft which will cover ranges of more than 1500 nm and accommodate 80 to 130 passengers. These far exceed the capability of today's commuter types. In the required thrust range of 15-5-20 klb only a very limited number of older engines with high SFC is available. Recently the manufacturers have begun offering new turbofans based on modern core technology and internal mixing (long duct) with lower SFC.

The underwing turbofan installation aspects are well understood from earlier wide and narrowbody aircraft but installing a long-duct nacelle on such a small aircraft means a significant increase in interference problems which may lead to close coupling and new methods for minimisation of the mutual interference.

After a survey of installation problems on previous jet transports up to the Airbus family the state of the art of experimental and theoretical methods for interference analysis is discussed. By means of an inverse design method a local lofting change on a given wing design confined to 20% span area was derived in order to sustain the isobar pattern of the clean wing with the pod/pylon on.

The design modification was checked by means of a 3D-Euler code and verified on a large half-model in the NLR-HST wind tunnel. From the analysis of the resulting conclusions concerning the feasibility of such a lofting change, further improvements are made.

Type
Research Article
Information
The Aeronautical Journal , Volume 97 , Issue 961 , January 1993 , pp. 1 - 13
Copyright
Copyright © Royal Aeronautical Society 1993 

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. Ott, J. Civil aviation must tackle major challenges in 1990s, Av Week Space Technol, 20 November 1989.Google Scholar
2. Interavia Airletter, 28 February 1991, 12, (193), p 7.Google Scholar
3. Interavia Airletter , 27 February 1991, 12, (192), p 6.Google Scholar
4. Pilling, M. The 90-120 seat jet race is on, Interavia Aero Rev, 1990, (8).Google Scholar
5. Middleton, P. MPC gears up, Flight Int , 8 April 1989.Google Scholar
6. Interavia Airletter , 5 March 1991, 12, (196), p 6.Google Scholar
7. Greff, E. Aerodynamic design for a new regional aircraft ICAS-90- 2.7.1, Stockholm, Sweden.Google Scholar
8. Obert, E. The aerodynamic development of the Fokker 100 ICAS- 88-1.6.2, Jerusalem, Israel.Google Scholar
9. Fischer, B. Configurational repercussions of new technologies in the design of a regional airliner, AIAA paper 89-2022.Google Scholar
10. Henne, P. A. MD-90 transport aircraft design AIAA paper 89-2023.Google Scholar
11. Interavia Airletter , 13 March 1991, 12, (202), p 6.Google Scholar
12. Losch, S. Influence of flow mixing on the performance of a turbofan engine of high bypass ratio, ZFlugwiss, 1990, 14, pp 333–341.Google Scholar
13. Dupslaff, M., Wehlitz, P. and Schimmino, P. Propfan technology, In: European Forum: The Evolution of Regional Aircraft Technologies and Certification. Organised by DGLR, AAF and RAeS, 6-7 April 1989, Friedrichshafen.Google Scholar
14. Swan, W. C. and Sioalla, A. The problem of installing a modern high bypass engine on a twin jet transport aircraft, AGARD CP-124, April 1973.Google Scholar
15. Lynch, F. T. Commercial transports-aerodynamic design for cruise performzance efficiency, Prog Astronaut Aeronaut, Summerfield, M. (Ed), 1982, 81.Google Scholar
16. Krenz, G.Engine/Airframe Interference, AGARD-FDP-VKI Special Course, May 1983.Google Scholar
17. Henderson, W. P. and Patterson, J. C. Jr Propulsion installation characteristics for turbofan transports, AIAA paper 83-0087, 1983.Google Scholar
18. Kutney, J. T. and Piszkin, S. P. Reduction of drag rise on the Convair 990 airplane, J A ircra, 1964, 1, (1).Google Scholar
19. Tinoco, E.N. Transonic CFD applications at Boeing, Transonic Symposium — Theory, Application, and Experiment, 19-21 April 1988, NasaLangley.Google Scholar
20. Haftmann, B. and Kiekebusch, B. Details zur Optimierung des Reiseflugwiderstandes des Airbus A320, DGLR-Jahrestagung 85-89, September 1985, Bonn.Google Scholar
21. Mirat, J. J., Perin, R. and Castan, C. Engine installation design for subsonic transport aircraft, ICAS-90-2.7.4, Stockholm, Sweden.Google Scholar
22. Tinoco, E. N. and Chen, A. W. CFD applications to engine/airframe integration, ProgAstronaut Aeronaut:NumericalMethods for Engine-Airframe Integration, Summerfield, M. (Ed.), 1986, 102, pp 219–255 Google Scholar
23. Bowes, G. M. Aircraft lift and drag prediction and measurement, AGARD-LS-67, May 1974.Google Scholar
24. Harris, A. E. and Paliwal, K. C. Civil turbofan propulsion system integration studies using powered testing techniques at ARA, AIAA paper No. 84-0593, 1984.Google Scholar
25. Ewald, B. Transport configuration wind tunnel tests with engine simulation, AIAA paper 84-0592, 1984.Google Scholar
26. Eckert, D. and Burgsmuller, W. Simulation und Messung von Triebwerkseinfliissen an einem zweistrahligen Flugzeugmodell mit Hilfe von Modelltriebwerken, DGLR-Jahrestagung 85-92, September 1985, Bonn.Google Scholar
27. Burgsmuller, W., KOOI, J. W. and MOLLF.R, K. W. Accuracy requirements for high-speed test with engine simulation on transport aircraft models in the NLR-HST, AGARD CP 429, Fluid Dynamics Symposium, Naples, Italy, 1987.Google Scholar
28. Flaig, A. Results of wind tunnel ground effect measurements on Airbus A320 using turbine power simulation and moving tunnel floor techniques, AIAA paper 90-1427, 1990.Google Scholar
29. Ehrmann, M., Klevenhusen, K. D., Rudolph, K. and Burgsmcller, W. Computation of engine-airframe interference flows at subsonic and transonic speeds, ICAS paper No. 84-2.10.1, Toulouse, 1984.Google Scholar
30. Yaros, S. F., Carlson, J. R. and Chandrasekaran, B. Evaluation of three numerical methods for propulsion integration studies on transonic transport configurations, NASA TM-87727, June 1986.Google Scholar
31. Lord, W. K. and Zysman, S.H. VSAERO analysis of a wing/Ipylon/nacelle configuration, AIAA paper No. 86-1523, 1986.Google Scholar
32. Sauer, G. and Szodruch, J. Untersuchung des Triebwerkeinflusses an Fliigeln mit modernen Hochbypass-Antriebskonzepten, DGLR- Jahrestagung 1987, Berlin.Google Scholar
33. Atta, E. H. and Vadyak, J. Numerical simulation of the transonic flowfield for wing/nacelle configurations, J Aircra, 1986, 23, (1).Google Scholar
34 Chen, A. W., Curtin, M. M., Carlson, R. B. and Tinoco, E. N. TRANAIR applications to engine/airframe integration, J. Aircra, 1990, 27, (8).Google Scholar
35. Ronzheimer, A., Rossow, C. C. and Pflug, M. Untersuchungenzum Interferenzeinfluβ von modernen Hochbypass-Antrieb-skonzepten an einer Flügel-Rumpf (Combination durch Lösung der Eulergleichungen,DGLR-Jahrestagung90-108,October 1990, Friedrichshafen.Google Scholar
36. Rill, S. and Becker, K. Simulation of transonic inviscid flow over a twin jet transport aircraft, AIAA paper 91-0025, 1991.Google Scholar
37. Tinocco, E. N. Applied computational aerodynamics, Prog Astronaut Aeronaut, Henne, P. A. (Ed.), 1990, 125, pp 571–578.Google Scholar
38. Rossow, C. C. Efficient computation of inviscid flow fields around complex configurations using a multi-block multigrid method, 5th Copper Mountain Conference on Multigrid Methods, 31 March- 5 April 1991.Google Scholar
39. Rill, S. and Becker, K. Melina — a multiblock, multigrid 3d euler code with sub block technique for local mesh refinement, ICAS-92- 4.3.R, Beijing, China.Google Scholar