Investigation Of Drag And Lift Force On An Airfoil Shaped Body At Different Angles
Experimental investigation of drag and lift force on an airfoil shaped body at different angles is presented.
Fundamentals of aircraft design is provided with detailed estimation of the aerodynamic drag of airfoil is presented. These
include the definition of the mission of the aircraft and various requirements, such as performance, handling, manufacturing,
upgradability, maintainability, and many others. At different angle the coefficient of drag is to determine. A 3D airfoil was
placed in a low speed wins tunnel with pressure taps along its surface and a pitot probe downstream to measure the flow
characteristics. The wind tunnel was operated at nominal velocities during the coefficient measurement, a Reynold’s number
of about 200- 800. The airfoil, with a 10inch chord, was analyzed at 0,5,10,15,20,25 degrees angles of attack and with
different loads. The phenomenon known as hysteresis with regards to stall conditions was also observed by varying the angle
of attack and wind tunnel velocity.