![]() The function name should be lab5, the input should be a string with the filename of the data, and the output should be the lift array (which is calculated using your own trapezoidal function). ![]() Finally, convert your script to a function to test it here on Grader. Your plot and lift array should be the same. Once you have this function written, replace your trapz calls from part 3 with a call to your own function. The result of the integral approximation (a scalar value) should be the output of the function. The function should numerically integrate f over x using the trapezoidal rule. The function should have two inputs (x and f, use any variable names you'd like though), the same two inputs that trapz has. Instead of using the trapz function, write your own function that calculates the integral using the trapezoidal rule. Create this plot (required for grading: square filled markers only, xlabel, ylabel, grid): Calculate the lifting force using the the built-in function trapz using the following formula: Fx =sin(90 – a)(/ pBOTdx+ / propax) Do this for four angles of attack a= 0°, 4°, 8°, 16° angle of attack data. Q = 0° a = 4° Pressure Pressure Bottom Top Bottom - Top - Ta O 0.5 Airfoil chord a = 8° 0.5 Airfoil chord length (%) a = 16° o Pressure Pressure T Bottom Top Bottom - Top ♡ O 0.5 1 Airfoil chord length (%) 0 0.5 1 Airfoil chord length (%) 3. Notice the high pressure at the bottom of the airfoil and low pressure at the top of the airfoil, which is what produces lift.and makes airplanes fly. ![]() Recreate this figure so you can get familiarized with the data (required for grading: 4 subplots (each with two lines), 4 titles, legends). In this lab, you will look at some pressure data and calculate lift. When pressure along the bottom of the wing is greater than pressure on top of the wing, you get lift! The angle of attack, can be adjusted to increase lift. The pressure can be measured in the lab by placing pressure taps along the airfoil (right diagram above). Air is a fluid that has various properties like density and pressure. There are links to the original airfoil source and dat file and the details page with polar diagrams for a range of Reynolds numbers. Click on an airfoil image to display a larger preview picture. At high speeds, there is airflow that moves over and under the wing (airfoil) as can be seen in the left diagram above. Airfoil database search (NACA 6 series) Search the 1638 airfoils available in the databases filtering by name, thickness and camber. Pressure taps at top of airfoil (0-14) BY X X/C 0.6 a, angle of attack Pressure taps at bottom of airfoil (15-29) An airfoil is a cross section of an airplane wing. mat file holds 9 variables: x is the distance along the airfoil, pBOT_0 is the pressure along the bottom of the airfoil when the angle of attack is oº, PTOP_0 is the pressure along the top of the airfoil when the angle of attack is 0°, pBOT_4 is the pressure along the bottom of the airfoil when the angle of attack is 4°, PTOP_4. Load the data into your workspace (in a script file). Download the data file, airfoil.mat and place in your working directory.
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