A model of an inflatable elastic aerofoil

Abstract A novel method is presented to calculate the deformation of a simple elastic aerofoil with view determining its aerodynamic viability. The modelled as thin two-dimensional sheet whose ends are joined together form corner prescribed angle, support included constrain shape resemble that classical aerofoil. weight counterbalanced exactly by lift force due circulation set according Kutta condition. An iterative process based on boundary integral used compute in response an inviscid fluid flow, and range flow speeds determined for which maintains shape. As speed increased deforms significantly around trailing edge, resulting negative camber loss lift. ameliorated increasing inflation pressure but at expense increase drag bulges into less Boundary layer calculations nonlinear unsteady viscous simulations analyse characteristics deformed flow. By tailoring internal separation can be delayed lift-to-drag ratio substantially increased.