Open Science Research Excellence
%0 Journal Article
%A Dinesh M. and  Kenny Mark V. and  Dharni Vasudhevan Venkatesan and  Santhosh Kumar B. and  Sree Radesh R. and  V. R. Sanal Kumar
%D 2014 
%J  International Journal of Mechanical, Aerospace, Industrial, Mechatronic and Manufacturing Engineering
%B World Academy of Science, Engineering and Technology
%I International Science Index 96, 2014
%T Diagnostic Investigation of Aircraft Performance at Different Winglet Cant Angles
%V 96
%X Comprehensive numerical studies have been carried
out to examine the best aerodynamic performance of subsonic aircraft
at different winglet cant angles using a validated 3D k-ω SST model.
In the parametric analytical studies NACA series of airfoils are
selected. Basic design of the winglet is selected from the literature
and flow features of the entire wing including the winglet tip effects
have been examined with different cant angles varying from 150 to
600 at different angles of attack up to 140. We have observed, among
the cases considered in this study that a case, with 150 cant angle the
aerodynamics performance of the subsonic aircraft during takeoff
was found better up to an angle of attack of 2.80 and further its
performance got diminished at higher angles of attack. Analyses
further revealed that increasing the winglet cant angle from 150 to 600
at higher angles of attack could negate the performance deterioration
and additionally it could enhance the peak CL/CD on the order of
3.5%. The investigated concept of variable-cant-angle winglets
appears to be a promising alternative for improving the aerodynamic
efficiency of aircraft.

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