International Journal of Vehicle Structures and Systems

The PDF file you selected should load here if your Web browser has a PDF reader plug-in installed (for example, a recent version of Adobe Acrobat Reader).

If you would like more information about how to print, save, and work with PDFs, Highwire Press provides a helpful Frequently Asked Questions about PDFs.

Alternatively, you can download the PDF file directly to your computer, from where it can be opened using a PDF reader. To download the PDF, click the Download link above.

Fullscreen Fullscreen Off

   Subscribe/Renew Journal


Icing is a challenging problem in the aerospace environment especially for inter-continental airline operations. Existing anti-icing methods offer consistent performance against glaze icing problems however it compromises the fuel efficiency through by-pass bleed air. A Numerical analysis for an airfoil with and without icing conditions is done to investigate the velocity distribution around the commercial airplane wing. The supercritical airfoil is analyzed in step by step ice accretion aspect under optimal velocity input about 175 m/s. The surrounding temperature is maintained in the range of 273K to 243K as per FAR standards at various angles of attack. The airfoil is designed by DESIGN MODELER module exists in ANSYS workbench and it is meshed with ICEMCFD. Subsequently, it is analyzed with the help of a flow solver at various time steps of ice accretion to verify the dynamic pressure changes due to rime icing. The iced airfoil produced realistic CL and CD variations for different ice shapes against the clean wing configuration. The step by step ice accretion is summarized and the roadmap for ice elimination through coating techniques is proposed.

Keywords

Icing Problem, Velocity Distribution, Fluent, Wind Tunnel Testing.
User
Subscription Login to verify subscription
Notifications
Font Size