The aim of the study is to investigate how choice airfoil affects aerodynamic characteristics a flying wing UAV. For this purpose, comparative analyzes were performed for four different airfoils: MH60, TL54, Eppler 339, and TsAGI 12%. Given maximum range performance (maximum lift /drag ratio), best efficiency given by UAV with MH60 TL54 airfoil. Based on their lift-to-drag ratio, UAVs made airf...

In most cases authors are permitted to post their version of the article (e.g. in Word or Tex form) to their personal website or institutional repository. Authors requiring further information regarding Elsevier's archiving and manuscript policies are encouraged to visit: Abstract A transversely oscillating cylinder in a uniform flow is modeled to investigate frequency effects of flow-induced w...

the purpose of this study is to improve the aerodynamic performance of wind turbine blades, using the ball-spine inverse design method. the inverse design goal is to calculate a geometry corresponds to a given pressure distribution on its boundaries. by calculating the difference between the current and target pressure distributions, geometric boundaries are modified so that the pressure differ...

We show by computational solution of the incompressible Navier-Stokes equations with friction force boundary conditions, that the classical inviscid circulation theory by Kutta-Zhukovsky for lift and laminar viscous boundary layer theory by Prandtl for drag, which have dominated 20th century fluid dynamics, do not correctly describe the real turbulent airflow around a sail under tacking. We sho...

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Miniflaps at the trailing edges of airfoils (e.g., Gurney flaps or divergent trailing edges) change the Kutta condition and thus produce higher lift. Unfortunately, however, the drag is also increased due to the flow separation downstream of this particular type of trailing edge. Therefore, the trade-off between beneficial and detrimental effects is considered in this paper. Various aspects of ...

A new annular lift fan configuration that has very high lift efficiency is explored by using a numerical scheme. The inlet lip radius and diffuser angle are maximized by semicircle duct walls and the location of the lift fan is moved from the throat to the diffuser area to maximize the diffusion effect of the ducted fan. The improved lift fan achieves the figure of merit of 0.772 and the power ...

Abstract In this paper, the prediction of unsteady flow field over typical high aspect ratio (AR) wings in transonic regime but below sonic Mach number is interest. The methodology adopted a computational approach based on small disturbance potential equation. It shown that higher AR generally have lift coefficient as well lift-to-drag ratio. With NASA’s common research model (CRM) wing, there ...