AERODYNAMIC PERFORMANCE STUDY OF AEROFOIL USING BLOWING SUCTION PIPE VENT SYSTEM

Abstract

This research work carried out a numerical study of aerofoil performance with vertical hole   to evaluate the aerodynamic performances using novel method called Blowing Suction pipe vent (BSPV) method at takeoff landing and cruise conditions. The simulation study was conducted by Reynolds averaged Navier stokes equation solver with the turbulence model of k epsilon. There are two different parameters were studied like injection suction slot location and injection angle to study the effect of various aerodynamic parameters like lift, drag, pressure coefficient. The results shows that the proposed blowing suction pipe vents design enhance the aerodynamic parameters of stall angle and lift coefficient of 50% and 60% compared with existing aerofoil with reduction of drag. The injection angle of 15 degree playing the major role to influence the aerodynamic parameters. The important conclusion is to place the injection at top surface and suction at bottom surfaces efficiently control the boundary layers at various flight phases which can be suitable for all aircraft.