This chapter introduces aspects of inviscid flow analysis that enable velocity at any part of the flow, around a wing for instance, to be defined. Knowing that the flow component normal to surface of an aerofoil must be zero, the entire flow and resulting pressure distribution can be determined. The chapter introduces the analysis of the flow around two‐dimensional thin aerofoils. The classical two‐dimensional inviscid flow theory provides a basis for analyzing flow motion. A more accurate representation of any fluid motion can be provided by including rotational flow; this can be defined in terms of the vorticity, which is a measure of the angular velocity or spin within the fluid. The chapter extends the panel method approach in concept to model the aerodynamic forces resulting from unsteady harmonic motion. The use of a panel aerodynamics method has been illustrated using a simple two‐dimensional aerofoil and three‐dimensional wing model.
Potential Flow Aerodynamics
2014-12-02
22 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
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