Effect of Tubercle Leading Edge Control Surface on the Performance of the Double Delta Wing Fighter Aircraft
Journal Title: International Journal for Research in Applied Science and Engineering Technology (IJRASET) - Year 2015, Vol 3, Issue 6
Abstract
To improve the aerodynamic characteristics of the generic fighter aircraft by modifying the leading edge control surface of the tailless double delta wing. Simulations are carried out to determine the lift to drag ratio and pitching moment characteristics of the modified wing (Tubercle LEVCON) and compared with the existing fighter aircraft wing at low Mach numbers and high angles of attack, typically for landing/ takeoff configurations. The computational domain is meshed with unstructured grids and steady state Reynolds Averaged Navier Stokes (RANS) CFD simulations are carried out. Lift coefficient and drag coefficient are considered as the principle performance metrics for a control surface and pitching moment is determined for assessing the performance and longitudinal stability of the aircraft. Results obtained indicate that the tubercle wing increases the lift coefficient due to the vortex formation at each tubercle and the flow remains attached over the entire span of the wing.
Authors and Affiliations
P Sharmila, S Rajakumar
Keywords
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- EP ID EP20949
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