Abstract
A stability analyzer for transition prediction over arbitrary three-dimensional wings operating in the transonic regime is proposed. This analyzer is used to illustrate the importance of including the effects of spanwise pressure gradient in transition predictions over such configurations. To this end, three calculation methods were employed: 1) a three-dimensional Euler solver, 2) a three-dimensional boundary-layer solver, and 3) a numerical method for the solution of the linear stability equations based on the temporal formulation. The influence of spanwise pressure gradients is illustrated by the application of this stability analyzer to the flow about the NASA AMES and ONERA-M6 wings. The pertinence of using a fully three-dimensional method rather than the simpler conical-flow calculations is demonstrated. The differences between the fully three-dimensional and conical-flow results are of the same order as the curvature or nonparallel effects
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.
