Abstract
Wind tunnel tests have shown that it is feasible to design high performance supercritical wing sections by solving mathematically the inverse problem of shaping an airfoil so that the transonic flow over it becomes shockless at specified conditions. The construction of shockless flows is most effectively carried out by means of the hodo-graph method based on complex characteristics that has been described in Chapter II. For practical applications it is essential to combine the method with a reliable turbulent boundary layer correction so as to completely suppress separation and any loss of lift associated with it.
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© 1977 Springer-Verlag Berlin Heidelberg
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Bauer, F., Garabedian, P., Korn, D. (1977). Transonic Airfoil Design Code. In: Supercritical Wing Sections III. Lecture Notes in Economics and Mathematical Systems, vol 150. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-642-48852-8_3
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DOI: https://doi.org/10.1007/978-3-642-48852-8_3
Publisher Name: Springer, Berlin, Heidelberg
Print ISBN: 978-3-540-08533-1
Online ISBN: 978-3-642-48852-8
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