NUMERICAL INVESTIGATION OF FLOW CHARACTERISTICS OF A NON-SLENDER LAMBDA WING UNMANNED AERIAL VEHICLE

In this paper, the low-speed aerodynamic performance of lambda wing with a chord length c=210 mm and sweep angle Λ =51°, thickness 3 mm, beveled leading edges on windward side an 58° is investigated numerically. Reynolds Average Navier Stokes (RANS) theorem equations Spalart-Allmaras turbulence model were solved up to attack 45° for incompressible flow around surface and, are compared experiment corralete simulation precision computational fluid dynamic approaches. Detail about including development formation leading-edge vortex (LEV), interaction surface, separations, stall studied, presented, discussed. LEV was started at 5°, breakdown observed halfway along edge 20°, finally, by time 30°, bursting gives way stage.