Abstract
A high-order improvement to an unstructured viscous CFD solver is evaluated and applied to the computation of helicopter rotors in hover and forward flight. The high-order improvement is achieved by reconstructing flow variables at interface of each control volume through high-order polynomial approximations. The reconstructed interface variables are used as the basis values to evaluate the high-order fluxes on the sub-faces of each interface of the control volume using a radial basis function interpolation. The improvement on the unstructured scheme is evaluated for an inviscid unsteady vortex travelling with a free stream flow for the observed order of accuracy. The high-order improvement method is also applied to compute a realistic helicopter rotor in hover and forward flight. Numerical studies indicate that the current high-order improvement is effective in preserving the vortex strength generated by helicopter blades and thus improves the numerical accuracy of predictions.
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.
