Abstract
Analytical solutions are derived for a class of two-dimension al transonic cascade flows. In the particular limiting case studied, the airfoils are considered as lightly loaded; a similarity parameter is defined for this case. Second-order asymptotic solutions are derived for the nearly one-dimensional flow in regions directly between successive airfoils and for the periodic flow ahead of and behind the cascade. For high subsonic Mach numbers, composite solutions are obtained by a suitable joining of these results with solutions derived for thin regions containing the leading and trailing edges. Surface pressures and lines of constant Mach number are calculated for circular-arc airfoils in some specific examples. For low supersonic speeds a far-field solution, which allows calculation of the decay of shock waves at large distances, is also derived.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
