Abstract
A method for designing airfoil profiles of specified trailing-edge thickness corresponding to given arbitrary supercritical speed distributions is described in this paper. It is known that the surface speed must satisfy three constraints in order for a solution to exist. Hence, to guarantee satisfaction of the constraints in our method, the speed distribution is specified with three free parameters whose values are found automatically. The modifications introduced to an ideal target speed distribution are everywhere smooth and avoid the occasional''spikes that were present in an earlier version of the method. The new functional forms used to modify the ideal target are well behaved at all times and prevent undue excursions of the airfoil profile during the iteration process. As a result, the iteration is much faster than in the earlier version of the method and it is now possible to quickly design airfoil shapes that are shockless or have shocks on the surface or off in the field.
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.
