ANOTHER paper Ref. 1 establishes a new approximate solution of the boundary layer equations devised to meet difficulties that are encountered in applying earlier solutions to laminar flow aerofoils and similarly thin cylinders. The advantage is in respect sometimes of accuracy, sometimes of applicability. The solution is a little unwieldy in its general form, however, and the present paper describes simplifications to facilitate rapid technical use. They are of two kinds, one being much more drastic than the other, and that first given, or both, may be used according to the nature of the problem and the accuracy required. Examples suggest that the resulting loss of accuracy and applicability will be small in most instances. This matter is described in Section I.
Aircraft Engineering and Aerospace Technology – Emerald Publishing
Published: Jan 1, 1949
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