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Linear Aerodynamics of Wings and Bodies

  • Josef Rom

Abstract

The beginnings of modern mathematical analysis of Fluid Mechanics may be attributed to Euler (1707–1783). The differential equations representing the conservation rules of mass, momentum and energy for inviscid potential flows are known as Euler equations. Analytical solutions to Euler equations have been obtained for some two-dimensional and a few three-dimensional flow problems. For small disturbances in subsonic (below the critical Mach number) and supersonic flows, the equations for the perturbation velocities can be linearized, and exact or approximate analytical or numerical solutions can be developed. Small disturbance conditions require that aerodynamic configurations consist either of thin lifting surfaces and/or slender elongated bodies at small angles of attack. Linearized potential equations for subsonic and supersonic flows, the Laplace and the Wave equations, respectively, can be solved by superposition of elementary solutions of the corresponding subsonic or supersonic singularities — source, doublet and/or vortex. The full potential flow equations for transonic speeds, which are inherently nonlinear, can be solved by numerical methods.

Keywords

Control Point Supersonic Flow AIAA Paper Lift Coefficient Vortex Lattice 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

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Copyright information

© Springer-Verlag New York, Inc. 1992

Authors and Affiliations

  • Josef Rom
    • 1
  1. 1.Department of Aerospace EngineeringTechnion-Israel Institute of TechnologyHaifaIsrael

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