Summary
The paper presents a panel method which allows to design 3-dimensional configuration with prescribed pressure distribution at specified design angles of attack. Effects of flaps deflection can be incorporated and the induced drag can be minimized. A higher order panel method is applied to perform flow analysis. Flaps deflection is simulated by modifying a Neumann boundary conditions. In the design case the geometry which minimizes differences between the design and actual pressure distributions and/or minimizes induced drag is found iteratively using an optimization technique. Geometrical constrains and regularity conditions can be specified by means of penalty function concept and the requested values of lift and moment coefficients can be enforced using Lagrange multipliers technique.
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References
K. Kubrynski, Design of 3-Dimensional Complex Airplane Configurations with Specified Pressure Distribution via Optimization, Proceedings of ICIDES-III Conference, G.S. Dulikravich, Washington D.C. (1991).
K. Kubrynski, Two-Point Optimization of Complete Three-Dimensional Airplane Configuration, AIAA 10’th Applied Aerodynamics Conference,AIAA 92–2618 (1992).
G. N. Ward, Linearized Theory of Steady High-Speed Flow, Cambridge University Press (1995).
D. R. Bristow, G. G. Grose, Modification of the Douglass Neumann Program to Improve the Efficiency of Predicting Component Interference and High Lift Characteristics, NASA CR-3020 (1978).
F. T. Johnson, A General Panel Method for the Analysis and Design of Arbitrary Configurations in Incompressible Flow, NASA CR-3079 (1980).
S. Heiss, L. Fornasier, Analysis of a Fighter Type Aircraft Configuration with the HISSS Panel Method at Subsonic and Supersonic Speeds, Z. Flugwiss. Weltraumforsch. 12 (1998), pp.224–232.
S. A. Moyer, PAN AIR Analysis of Simply Connected Control Surface Deflections, J. Aircraft, Vol.30 No. 1 (1993).
M. Drela, XFOIL: An Analysis and Design System for Low Reynolds Number Airfoils, in Low Reynolds Number Aerodynamics, Ed. T. J. Mueller, Lecture Notes in Eng. 54 (1989).
J. M. J. Fray, J. W. Slooff A Constrained Inverse Method for the Aerodynamic Design of Thick Wings with Given Pressure Distribution in Subsonic Flow, AGARD CP-285 (1980).
I.Kroo, S.C.Smith, The Computation of Induced Drag with Nonplanar and Deformed Wakes, SAE Technical Paper Series, No. 901933 (1990).
D. R. Bristow, J. D. Hawk, Subsonic Panel Method for the Efficient Analysis of Multiple Geometry Perturbations, NASA CR-3528 (1982).
L.M.M.Boermans, D.C.Terleth, Wind Tunnel Tests of Eight Sailplane Wing-Fuselage Combinations, Technical Soaring, Vol. VIII, No. 3 (1984).
L.M.M.Boermans, K.Kubrynski, Aerodynamic Design of Sailplane Wing-Fuselage Combinations, Paper presented at 23 OSTIV Congress, Botlange, Sweeden (1993).
J.W.Sloof, Application of Computational Procedures in Aerodynamic Design, AGARD, R-712 (1983).
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© 1999 Friedr. Vieweg & Sohn Verlagsgesellschaft mbH, Braunschweig/Wiesbaden
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Kubrynski, K. (1999). Subsonic Aerodynamic Design Via Optimization. In: Fujii, K., Dulikravich, G.S. (eds) Recent Development of Aerodynamic Design Methodologies. Notes on Numerical Fluid Mechanics (NNFM), vol 65. Vieweg+Teubner Verlag. https://doi.org/10.1007/978-3-322-89952-1_3
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DOI: https://doi.org/10.1007/978-3-322-89952-1_3
Publisher Name: Vieweg+Teubner Verlag
Print ISBN: 978-3-322-89954-5
Online ISBN: 978-3-322-89952-1
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