Abstract
A design-oriented method for evaluating the leading-edge (LE) thrust force on supersonic lifting surfaces with subsonic LE is presented. The method is developed to overcome numerical noise and nonsmooth drag predictions observed when currently attainable LE-thrust techniques are used for wing planform shape optimization. The method is an extension of a design-oriented unsteady supersonic lifting surface capability developed previously for aeroservoelastic shape optimization of wings. It is a panel/lattice method where assumed pressure-weighting functions, taking the LE singularity into account, are prescribed to the LE panels while constant pressure panels are retained elsewhere. Explicit expressions for aerodynamic influence coefficients are retained over most of the wing, except for cases involving the LE panels, where numerical integration must be used. Planform shape sensitivities of the LE thrust and wing pressures are obtained using a combination of analytic and semianalytic techniques.
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.
