Which model seems to provide the closest model for the actual Wright Flyer replica data?
Support your conclusion. Wind Tunnel Test Data As stated earlier, for takeoff to occur the lift force that must overcome the weight of the aircraft. Lift expected can be calculated from the coefficient of lift data obtained in the wind tunnel testing. The formula for this calculation is shown below. Lift = Coefficient of lift x Area of the wing x Dynamic air pressure This can be expressed using in the following manner using variables: FL = CL x S x q The wing area on the Wright Flyer is 500 ft2. The dynamic pressure in the tunnel will be 2.05 lb./ft2. (Note: You will notice that English units are used. Since the aeronautics industry began in the United States, the world accepts and uses the units commonly used in the United States.) Using the wind tunnel test data runs 43 and 44 and the formula above, complete the following table. Alpha Coefficient of Lift Lift • If the replica of the Wright Flyer weighs 750 lbs., what is the minimum angle of attack required to overcome the weight and
