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Leading edge separation: a comparison between interaction theory and Navier–Stokes computations
Author(s) -
Braun S,
Kluwick A,
Trenker M
Publication year - 2003
Publication title -
pamm
Language(s) - English
Resource type - Journals
ISSN - 1617-7061
DOI - 10.1002/pamm.200310140
Subject(s) - airfoil , inviscid flow , separation (statistics) , computation , bubble , reynolds number , leading edge , angle of attack , mechanics , flow separation , mathematics , flow (mathematics) , limiting , wing , enhanced data rates for gsm evolution , geometry , physics , computer science , turbulence , aerodynamics , algorithm , thermodynamics , engineering , statistics , mechanical engineering , telecommunications
We consider the two‐dimensional high/moderate Reynolds‐number flow around a slender airfoil at small angles of attack. Special emphasis is placed on leading edge separation and the associated breakdown of the steady solution of the governing equations. A comparison between the predictions of the viscous/inviscid interaction theory of marginal separation, see e.g. [3], and the results of Navier–Stokes computations with DLR's ‘TAU’–code [2] shows excellent quantitative agreement concerning the location, size of the separation bubble and even the limiting maximum value of the angle of attack, up to which solutions by means of the particular approaches can be found.