Design, Fabrication and Performance Evaluation of Low Speed Open Jet Wind Tunnel for Free Flight Test of a Glider

Abstract

With the development of in the field of aerodynamics, a test model of aircraft, UAVs, MAVs and other flying and moving vehicles needs to go under rigorous test in wind tunnel for stability, lift, drag and other aerodynamics parameters. Despite of development of CFD for flow simulation over a body, experimental setup with proper flow conditions is necessary for carrying out actual aerodynamics test. The study presents conceptual design, numerical simulation and experimental setup of low speed open jet wind tunnel of blower type having test section of 1.5 m in width and 0.8 m in height. The wind tunnel was able to produce 7 m/s of free jet at outlet where the test object can be placed. The flow field evaluation showed mean flow uniformity lies mostly below 5%. Experiments related to aerodynamic loading was also carried out in this wind tunnel. Similarly, control surface response of UAV was observed in this wind tunnel. The development of such open jet wind tunnel can be useful for simulation of flights and testing of aerodynamic forces in test model of aircrafts.