Linear theory yields a good approximation of the pressure distribution at locations where flow separation is not dominant and can be used to compute the pressure distribution of thin airfoil sections at a small angle of attack in flows at transonic and low‐supersonic Mach numbers. For subsonic as well as supersonic flight at small angles of attack, the two‐dimensional flow in which a flying vehicle is immersed can be treated as predominantly isentropic with small perturbations imposed by flow deflections. The chapter illustrates that a two‐dimensional sharp‐edge thin airfoil experiences a much higher pressure drag for given lift than the pressure drag of a typical low‐speed airfoil in subsonic flow. The linear theory applies to inviscid and potential flow and hence skin friction drag should be added to the pressure drag due to lift and thickness.
Thin Wings in Two‐dimensional Flow
2020-07-07
9 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
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