XIANG ZhengPing , DAI YuTing

DOI Number: N/A

Conference number: IFASD-2017-219

A solver has been developed within the OpenFOAM framework to compute large amplitude motion of a two-dimensional rigid airfoil. The aerodynamic force obtained with this code is successfully validated by experimental data. On the basis of this, the bifurcation point and the Limit Cycle Oscillations of the NACA0012 airfoil are simulated. Then ,using the nonlinear aerodynamic data calculated by CFD, a nonlinear aerodynamic identification method is developed based on neural network method. This method laid the foundation for the analysis of the limit cycle oscillation.

Read the full paper here

In Categories: 1.Events, IFASD 2017, Reduced Order Modeling
Email
Print
LinkedIn
The paper above was part of  proceedings of a CEAS event and as such the author has signed a publication agreement to have their paper published in the repository. In the case this paper is found somewhere else CEAS always links to the other source.  CEAS takes great care in making the correct content available to the reader. If any mistakes are found  in the listings please contact us directly at papers@aerospacerepository.org and we will correct the listing promptly.  CEAS cannot be held liable either for mistakes in editorial or technical aspects, nor for omissions, nor for the correctness of the content. In particular, CEAS does not guarantee completeness or correctness of information contained in external websites which can be accessed via links from CEAS’s websites. Despite accurate research on the content of such linked external websites, CEAS cannot be held liable for their content. Only the content providers of such external sites are liable for their content. Should you notice any mistake in technical or editorial aspects of the CEAS site, please do not hesitate to inform us.