This content is not included in
your SAE MOBILUS subscription, or you are not logged in.
Aspects of the Application of a Three Dimensional Panel Method Tool in the Design of a Light Aircraft
Technical Paper
2005-01-4161
ISSN: 0148-7191, e-ISSN: 2688-3627
Annotation ability available
Sector:
Language:
English
Abstract
This paper presents the computer implementation process of the Panel Method for aerodynamic analysis of three dimensional bodies with or without lift. The computer implementation consists in the creation of pre and post processing environments and a solver for the solution of the problem in external flow potential over three dimensional bodies with and without lift. For cases in which there’s no lift, a constant distribution of sources over the body (fusaleges, farings, etc.) is used, their intensities calculated in order to guarantee impermeability of the body. For cases in which there is lift, a constant distribution of sources and doublets are used on the body (wings, tails, etc.). The intensity of the sources is solved in the same manner as cases with no lift. Intensity of doublets is solved in order to satisfy the equality condition regarding pressure on the under and upper side of the trailing edge (Kutta Condition) of the body without lift. An analysis of the aircraft CEA-308 is shown in order to illustrate the use of the developed program in light aircraft projects.
Authors
- Paulo Henriques Iscold Andrade de Oliveira - Centro de Estudos Aeronáuticos Universidade Federal de Minas Gerais – CEA/EEUFMG Center for Aeronautical Studies of the Federal University of Minas Gerais – CEA/EEUFMG
- Marcos Vinícius Bortolus - Centro de Estudos Aeronáuticos Universidade Federal de Minas Gerais – CEA/EEUFMG Center for Aeronautical Studies of the Federal University of Minas Gerais – CEA/EEUFMG
Citation
de Oliveira, P. and Bortolus, M., "Aspects of the Application of a Three Dimensional Panel Method Tool in the Design of a Light Aircraft," SAE Technical Paper 2005-01-4161, 2005, https://doi.org/10.4271/2005-01-4161.Also In
References
- Arnold, M. “ Inverse Pressure Gradient Matching ” 1997 Sport Aviation Magazine
- Hess, J. L. 1972 “ Calculation of Potential Flow About Arbitrary Three-Dimensional Lifting Bodies ” Douglas Aircraft Company Long Beach, California 165
- Hess, J. L. Smith, A. M. O. 1966 “ Calculation of Potential Flow About Arbitrary Bodies ” Progress in Aeronautical Sciences 3 Pergammon Press New York 138
- Hoerner, S.F. “ Fluid - Dynamic Drag ” 1963 Publicação própria
- Milne-Thomson, L.M. 1958 “ Theoritical Aerodynamics ” Dover Publications Inc. New York 430
- Moran, J. 1984 “ An Introduction to Theorical and Computational Aerodynamics ” John Wiley and Sons New York 463
- Morino, L. et alli 1985 “Computational Methods in Potential Aerodynamics” Spring Verlag Oxford 733
- Oliveira, P.H.I.A. 1999 “Projeto da Aeronave CEA-308” Centro de Estudos Aeronáuticos da EEUFMG Belo Horizonte
- Schlichting, H. 1955 “ Boundary Layer Theory” McGraw-Hill International Nova Iorque 535
- Tinoco, E.N. Rubbert, P.E. 1985 “Panel Methods: Pan Air” Spring Verlag Oxford 41 91