An iterative decambering approach for the post stall prediction of wings using known section data as inputs is presented. The method can currently be used for incompressible flow and can be extended to compressible subsonic flow using Mach number correction schemes. A detailed discussion of past work on this topic is presented first. Next, an overview of the decambering approach is presented an...

The unsteady flow characteristics of a supercritical OAT15A airfoil with shock control bump were numerically studied by wall-modeled large eddy simulation. numerical method was first validated the buffet and nonbuffet cases baseline airfoil. Both pressure coefficient velocity fluctuation coincided well experimental data. Then, four different bumps tested. A height h/c = 0.008 location xB/c 0.55...

The efficiency of an airfoil can be improved by adjusting its surface. CFD software was used to investigate a 2D with and without spanwise semicircular groove on the upper NACA0012 airfoils grooves were analyzed using k-ω turbulence model. lift drag coefficients compared. To effect location efficiency, added in various locations compared smooth airfoil. flow velocity remained constant at 20 m/s...

This thesis investigates the hydrodynamic effects of biologically-inspired leading-edge tubercles. Two complementary studies examine the performance of three-dimensional hydrofoils based on the pectoral flippers of the Humpback Whale (novangilae megaptera). The first study uses a static foil, with application to conventional control surfaces– such as rudders or dive planes–found on marine vehic...

A slot formed between the slat and main wing of 2D high-lift device is used to accelerate convergence flow upper surface improve field quality. In order further enhance characteristics, this paper proposes a design method for multi-channel leading-edge slats based on grid channels. On one hand, specific shape shrinking expansion tube lift characteristics leading slat. other newly plays similar ...

This article discusses the enhanced lift-drag ratio of a geometrically modified National Advisory Committee for Aeronautics 0012 aerofoil at low Reynolds number 40000. The study involves validating Averaged Navier Stokes Transition Shear Stress Transport model analysis flow around subject with profile angles attack ranging from 0 to 10°. coefficient lift drag increased by 70% an angle 6°. exten...

In this numerical and statistical study, lift drag coefficient performances of NACA-0009 NACA-4415 airfoils were evaluated in accordance with various attack angle at constant velocity wind. Lift coefficients was numerically determined by computational fluid dynamics code ANSYS FLUENT. Analysis design calculations implemented using L16 orthogonal array based on Taguchi method. Angles airfoil typ...

We introduce and study a new containment relation in graphs – lift contractions. H is a lift contraction of G if H can be obtained from G by a sequence of edge lifts and edge contractions. We show that a graph contains every n-vertex graph as a lift contraction, if (1) its treewidth is large enough, or (2) its pathwidth is large enough and it is 2-connected, or (3) its order is large enough and...

In this study, the flow past a finite-length tapered cylinder is numerically investigated via finite-volume method with Reynolds numbers ranging from 50-250 and taper ratio l = 1.5. The corresponding lift drag coefficients, as well Strouhal are presented. factors related to discontinuity, through of 100 - 200, in coefficient, which wake structure cylinder, explained. Furthermore, influence on d...