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Parallel adjoint-based optimisation of a blended wing body aircraft with shock control bumps

Published online by Cambridge University Press:  03 February 2016

W. S. Wong ,
A. Le Moigne  and
N. Qin
W. S. Wong
Affiliation:
Department of Mechanical Engineering, University of Sheffield, Sheffield, UK
A. Le Moigne
Affiliation:
Department of Mechanical Engineering, University of Sheffield, Sheffield, UK
N. Qin
Affiliation:
Department of Mechanical Engineering, University of Sheffield, Sheffield, UK
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Abstract

An Euler optimisation for a BWB configuration with winglets incorporating an array of three-dimensional shock control bumps is carried out by employing an efficient adjoint-based optimisation methodology. A high fidelity multi-block grid with over two million grid points is generated to resolve the shape of the 3D shock control bumps, the winglet as well as the overall BWB shape, which are parameterised by over 650 design variables. In order to perform such a large aerodynamic optimisation problem feasibly, the optimisation tools such as the flow solver and the adjoint solver have to be parallelised with a good parallel efficiency. This paper reports the parallel implementation efforts on the adjoint solver; especially on the calculation of the sensitivity derivatives, which has to be looped over the total number of design variables. Results from the optimisation of the wing master sections, winglet aerofoil sections and the three dimensional bumps indicate a significant improvement regarding the aerodynamic performance against the baseline geometry for the given planform layout of the aircraft.

Type
Research Article
Information
The Aeronautical Journal , Volume 111 , Issue 1117 , March 2007 , pp. 165 - 174
Copyright
Copyright © Royal Aeronautical Society 2007 

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References

1. Portsdam, M.A., Page, M.A. and Liebeck, R.H., Blended wing body analysis and design, 1997, Paper AIAA-1997-2317, Aerospace Sciences Meeting and Exhibition, Reno, NV, USA.Google Scholar
2. Biksynovskym, A.L., Buzoverya, N.O., Gurevich, B.I., Denisov, V.E., Dunaevsky, A.I., Shkadov, L.M., Sorin, O.V., Udzhuzhu, A.J. and Zhurihin, J.P., Flying wing-problems and decisions, Aircr Design, December 2001, 4, pp 193–219.Google Scholar
3. Smith, H., College of Aeronautics Blended Wing Body Development Programme, 2000, ICAS Paper 1.1.4, International Council of the Aeronautical Sciences 2000 Conference.Google Scholar
4. Qin, N., Vavalle, A. and Le Moigne, A., Spanwise lift distribution for blended wing body aircraft, J Aircr, March-April 2005, 42, (2), pp 356–365.Google Scholar
5. Le Moigne, A. and Qin, N., Variable-fidelity aerodynamic optimisation for turbulent flows using a discrete adjoint formulation, AIAA J, July 2004, 42, (7), pp 1281–1192.Google Scholar
6. Qin, N., Vavalle, A., Le Moigne, A., Laban, M., Hackett, K. and Weinerfelt, P., Aerodynamic considerations of blended wing body aircraft, Prog in Aerospace Sciences, 2004, 40, (6), pp 321–343.Google Scholar
7. Le Moigne, A. and Qin, N., Aerofoil profile and sweep optimisation for a blended wing-body aircraft using a discrete adjoint method, Aeronaut J, 2006, 110, (1111), pp 589–604.Google Scholar
8. Morris, A., Mob a European distributed multi-disciplinary design and optimisation project, 2002, Paper AIAA-2002-5444, Ninth AIAA/ISSMO Symposium on Multidisciplinary Analysis and Optimization, Atlanta, GA, USA.Google Scholar
9. Qin, N., Zhu, Y. and Shaw, S.T., Numerical study of active shock control for transonic aerodynamics, Int J of Numerical Methods for Heat and Fluid Flow, 2004, 14, pp 444–466.Google Scholar
10. Fulker, J.L. and Simmons, M.J., An experimental study of shock control methods, 1994, DRA/AS/HWA/TR94007/1.Google Scholar
11. Dima, C. and De Matteis, P., Effects of shock and boundary-layer control techniques on transonic flows about airfoils, 2000, Paper AIAA-2000-0517, 38th Aerospace Sciences Meeting and Exhibition, Reno, NV, USA.Google Scholar
12. Birkemeyer, J., Rosemann, H. and Stanewsky, E., Shock control on a swept wing, J Aerospace Sci and Tech, 2000, pp 147–156.Google Scholar
13. Stanewsky, E., Delery, J., Fulker, J.L. and De Matteis, P., Drag reduction by shock and boundary layer control, Results of the Project EUROSHOCK II, Notes On Numerical Fluid Mechanics and Multidisciplinary Design, 80, Springer.Google Scholar
14. Qin, N., Monet, D. and Shaw, S.T., 3D bumps for transonic wing shock control and drag reduction, 2002, CEAS Aerospace Aerodynamics Research Conference.Google Scholar
15. Holden, H.A. and Babinsky, H., Shock/boundary layer interaction control using 3D devices, 2003, Paper AIAA-2003-447, 41st Aerospace Sciences Meeting and Exhibition, Reno, NV, USA.Google Scholar
16. Qin, N., Wong, W.S. and Sellars, N., Validation and optimisation of 3D bumps for transonic wing drag reduction, 2005, CEAS/KATnet Conference on Key Aerodynamic Technologies, 20-22 June 2005, Bremen, Germany.Google Scholar
17. Wong, W.S., Qin, N. and Sellars, N., A numerical study of transonic flow in a wind tunnel over 3D bumps, 2005, Paper AIAA-2005-1057, 43rd Aerospace Sciences Meeting and Exhibition, Reno, NV, USA.Google Scholar