Hostname: page-component-7479d7b7d-qs9v7 Total loading time: 0 Render date: 2024-07-11T19:25:55.296Z Has data issue: false hasContentIssue false
  • English
  • Français

Supersonic wing-body wave drag co-ordinated optimisation based on FCE methodology

Published online by Cambridge University Press:  27 January 2016

X. Guan
X. Guan*
Affiliation:
Institute of System Engineering, CAEP Mianyang, China
*
gxh87222@163.com
Get access Rights & Permissions [Opens in a new window]

Abstract

Wave drag reduction is important for the aerodynamic performance optimisation of supersonic cruise aircrafts, such as the supersonic civil transport and the supersonic cruise missile. In this paper a method of the supersonic wing-body wave drag optimisation, the wave drag co-optimisation based on far-field composite elements (CoFCE), is proposed based on class-shape-transformation (CST) parameterisation. Wave drag optimisation cases of a supersonic civil transport wing-body are presented, including the optimisation results and computation cost analyses. It is suggested that the supersonic wing-body wave drag can be significantly reduced by the proposed method with relatively small numbers of design parameter. In the optimisation case presented in this paper a 45% wave drag reduction is achieved. The wave drag optimised configuration also achieved significant lift to drag ratio improvements in small angles-of-attack supersonic cruise flight conditions.

Type
Research Article
Information
The Aeronautical Journal , Volume 118 , Issue 1209 , November 2014 , pp. 1359 - 1372
Copyright
Copyright © Royal Aeronautical Society 2014 

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. Kulfan, B.M. Reynolds numbers considerations for supersonic fight, 2002, AIAA-2002-2838.Google Scholar
2. Kulfan, B.M. Fundamentals of supersonic wave drag, 2007, Fourth International Conference on Flow Dynamics, 26-28 September 2007, Sendai International Center, Sendai, Japan.Google Scholar
3. Kulfan, B.M. and Bussoletti, J.E. Fundamental parametric geometry representations for aircraft component shapes, 2006, AI-AA-2006-6948.Google Scholar
4. Kulfan, B. New supersonic wing far-feld composite-element wave-drag optimisation method, J Aircr, 2009, 46, (5), pp 1740–1758.Google Scholar
5. Guan, X.H. and Li, Z.K. and Song, B.F. Exploring optimization of supersonic wing thickness distribution using FCE (Far-feld composite element) method, J Northwestern Polytechnical University, 2012, 30, (2), pp 169–174.Google Scholar
6. Kulfan, R.M. Application of hypersonic favorable aerodynamic interference concepts to supersonic aircraft, AIAA-78-1458.Google Scholar
7. Ceze, M., Hayashi, M. and Volpe, E. A study of the CST parameterization characteristics, 2009, AIAA-2009-3767.Google Scholar
8. Kulfan, B.M. A universal parametric geometry representation method–CST, 2007, AIAA -2007-62.Google Scholar
9. Guan, X.H., Li, Z.K. and Song, B.F. A study on CST aerodynamic shape parameterization method, Acta Aeronautica et Astronautica Sinica, 2012, 33, (4), pp 625–633.Google Scholar
10. Kulfan, B.M. Recent extensions and applications of the ‘CST’ universal parametric geometry representation method, 2007, AI-AA-2007-7709.Google Scholar
11. Jones, R.T. Theory of wing-body drag at supersonic speeds, 1953, NACA-RM-A53H18A.Google Scholar
12. Jumper, E.J. Wave drag prediction using a simplifed supersonic area rule, J Aircr, 1983, 20, (10), pp 893–895.Google Scholar