Air Foil Lab Essays

4639 Words Dec 16th, 2014 19 Pages
Abstract:
In this experiment, the use of a scale model airfoil section of an aircraft wing will be analyzed in a wind tunnel. The basic physical laws of engineering and science shall be applied to verify and to understand the principles of flight. A dimensional analysis will be applied to the model airfoil to represent a full-scale wing prototype. The basics of aerodynamics, as applied to standard NACA airfoil configurations, shall be applied to establish performance data regarding lift, drag and stall with respect to the various angles attack demonstrated throughout the experiment at a number of air speeds.
It should be noted that the Cessna 152 trainer aircraft uses a NACA 2412 airfoil, which is slightly thinner than the NASA 2415
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Figure 1: Airfoil nomenclature………………….............................................................5 2. Figure 2: Wind Tunnel ……………….………………..…………………….…....…….6 3. Figure 3: Drag, lift and angle of attack ………………………….………….…....……..6 4. Figure 4: Upper and lower pressure coefficient using chord position.............................10 5. Figure 5: Graph showing lift force from different AOA…………………………….....11

LIST OF TABLES

1. Table 1: Distance of pressure sensing port and X/C ratio………………….…………13 2. Table 2: Surface area of upper and lower ports………..……………………………...13 3. Table 3: Upper Lift force at 789 RPM…………………………………………….......14 4. Table 4: Lower lift force at 789 RPM…………...……………………….…………....14 5. Table 5: Upper lift force at 1168 RPM………...…….…………………………….….15 6. Table 6: Lower lift force at 1168 RPM …………………………………….…....…....15 7. Table 7: Upper lift force at 1300 RPM……………………………………...………...16 8. Table 8: Lower lift force at 1300 RPM…………………………….......…....…...…...16 9. Table 9: Pressure coefficients of upper pin at 3 wind velocities…………….………..17 10. Table 10: Lower pressure coefficient at 3 wing velocities………………….….……..18 11. Total lift force at different velocity……………………….……….......…....….……..18

Introduction:
In aerodynamics, researchers have tried to find the most efficient way to produce the highest lift in an aircraft while reducing the drag generated on

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