Indian Journal of Science and Technology

Abstract

Objectives: The purpose of this study is a numerically investigation of aerodynamic characteristics of NACA0012 and Clark-Y airfoils with Local Flexible Membrane (LFM) in laminar and transient flows respectively. Novelty: A pressure based algorithm using a finite volume element method has been used to solve Navier-Stokes equations and the unique feature of the present method is the physical scheme influencing the convection fluxes at cell surfaces. Method: We have focused on the effects of deformation of the membrane on aerodynamic characteristics. First, we have solved the flow on NACA0012 airfoil in Reynolds number of 5000 and investigated the effects of LFM on aerodynamic coefficients in laminar flow. Then, we have solved the flow over Clark-Y airfoil in Reynolds number of 300000 and studied the effects of LFM in transient flow. To calculate the Reynolds stresses, transient γ - Reθ model has been used. Finding: According to the results, in laminar flow, the LFM prevents flow separation. In transient flow, the membrane by oscillation prevents flow separation, reduces drag coefficients, increases lift coefficients and delays the stall angle.
Keywords: Clark-Y, Finite Volume Element Method, Fluid-Solid Interaction, Local Flexible Membrane, NACA0012, γ - Reθ model