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WIND TUNNEL EXPERIMENTAL PROCEDURE

MAE 175A Wind TUNNEL Experiment (K. Seshadri) Written by Cattolica, modified by Tynan 1/10/2014 11 WIND TUNNEL EXPERIMENTAL PROCEDURE MAE 175A PART I Pressure Distribution over an airfoil and Drag by the wake survey method OBJECTIVE: Measure the pressure distribution over a Clark Y-14 Airfoil at various angles of attack and determine the drag coefficient of the wing by the wake survey method. Data are obtained up to and beyond the stall angle, where the flow separates from the upper surface of the airfoil. INTRODUCTION: An airfoil develops Lift through generally lower pressures above the wing and higher below with respect to the pressure of the approaching air. In addition, the Lift force increases with higher angle of attack up to a critical angle. Beyond this critical angle the lift force decreases significantly and the wing is said to have stalled.

Jan 10, 2014 · 1. Using the barometer and thermometer in the laboratory determine the density of the air flowing in the wind tunnel. 2. Using the Wing Tunnel Calibration VI calibrate the wind tunnel test section by generating a plot of velocity (m/sec) versus motor frequency (0- 60 Hz) using the upstream pitot-static tube and Bernoulli's equation.

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