Abstract
In recently published papers the authors have discussed the problem of drag of delta wings with straight trailing edges and also the lift of this type of wing. The present paper consists of an extension of these results to delta wings with swept-back or swept-forward trailing edges. Drag at zero lift for two slope surfaces and lift is computed for these airfoils, and a discussion is given of the drag due to lift. Centers of pressure are also computed. In addition, some results for drag of wings with three slope surfaces are given. Discussion is made of optimum design from the standpoint of leading and trailing edge angles, and location of maximum thickness. I t is shown that considerable improvements over two-dimensional airfoil performance can be obtained. Results are presented in the form of conventional engineering coefficients.
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.
