Hostname: page-component-745bb68f8f-b95js Total loading time: 0 Render date: 2025-01-27T19:18:51.620Z Has data issue: false hasContentIssue false
  • English
  • Français

EPISTLE: High lift system design for low-noise applied to a supersonic aircraft

Part of: Sustainable Aerospace

Published online by Cambridge University Press:  03 February 2016

U. Herrmann
U. Herrmann*
Affiliation:
DLR, Institute of Aerodynamics and Flow Technology, Braunschweig, Germany
Get access Rights & Permissions [Opens in a new window]

Abstract

A new approach for low-drag high-lift system design based on the application of viscous flow solvers was developed in the EC research project EPISTLE. Two high-lift systems for a supersonic commercial transport aircraft (SCT) wing were designed, manufactured and wind-tunnel tested. The predicted large drag reductions were fully confirmed by tests at high Reynolds numbers. These drag reductions significantly reduce the low-speed noise of future SCT configurations. This was estimated by preliminary aircraft design tools. Low-speed noise reduction by aerodynamic means is obtained, as effective high-lift systems enable these aircraft to climb faster.

Type
Research Article
Information
The Aeronautical Journal , Volume 110 , Issue 1107 , May 2006 , pp. 327 - 331
Copyright
Copyright © Royal Aeronautical Society 2006 

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. Lovell, D.A. European research of wave and lift dependent drag for supersonic transport aircraft. AIAA 99-3100. 1999.Google Scholar
2. Van Muijden, J. and Elsenaar, B. Numerical prediction capabilities and analysis of flow development for a supersonic civil transport at low speed. Proceedings of the CEAS Aerospace Aerodynamics Conference, Cambridge, 10-12 June 2002.Google Scholar
3. Brandi, V., Amato, M. and Catalano, P. Validation of CIRA Flow Solver ZEN for SCT Low-Speed High-Lift Computations. 23rd ICAS congress, Toronto, Canada, ICAS-2002-244, 2002.Google Scholar
4. Herrmann, U. and Figueiredo, H. CFD for supersonic civil transport high-lift evaluation and configuration development. GARTEUR TP-137, 2002.Google Scholar
5. Herrmann, U. Low-speed high-lift performance improvements obtained and validated by the EC-project EPISTLE. ICAS 2004-4.1.1. 24th ICAS congress, 29 August 2004 – 3 September 2004, Yokohama, Japan.Google Scholar
6. Herrmann, U. et al Validation of European CFD Codes for SCT low-speed high-lift computations. AIAA 2001-2405. 2001.Google Scholar
7. Brodersen, O., Hepperle, M., Ronzheimer, A., Rossow, C.-C. and Schöning, H.B.. The parametric grid generation system MegaCads. 5th international conference on numerical grid generation in computational Field simulation. National Science Foundation (NSF) pp 335–362. 1996.Google Scholar
8. Kroll, N., Rossow, C.-C., Becker, K. and Thiele, F. Megaflow – A numerical flow simulation system aerospace science technology, Jahrg. 4, (2000), pp 223–237.Google Scholar
9. Baldwin, B.S. and Lomax, H. Thin layer approximation and algebraic model for separated turbulent flows. AIAA Paper No. 78–257. 1978.Google Scholar
10. Degani, D. and Schiff, L. Computations of turbulent supersonic flows around pointed bodies having crossflow separation. J Computational Physics, 66, 1986, pp 173–196.Google Scholar