![]() The flow fields surrounding each of these airfoils are predicted using computational methods at a free stream Mach number of 0.17 and angles of attack between zero incidence and the onset of stall. Four airfoil geometries have been selected for study, three of which are supersonic geometries. Recently, interest in supersonic business jets has promoted many questions regarding how to accurately model these complex flow physics. These separated regions can have a large influence on the performance characteristics of the airfoil and are very sensitive to the ambient flow conditions. Separation bubbles form at very low angles of attack and grow tremendously as incidence is increased further. The sharp leading edge and mid-chord maximum thickness location of supersonic airfoils combine to create complex flow features at low speeds. Very few reports in the public domain address the flow characteristics of these airfoils at low subsonic speeds. Most aerodynamic studies of this class of airfoil focus primarily on the supersonic regime. "Supersonic airfoil geometries have been used since the 1940’s for high speed flight.
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