URGENT Problem 4.3 When calculating the lift and drag on an airfoil in an airstr
ID: 3796986 • Letter: U
Question
URGENT
Problem 4.3 When calculating the lift and drag on an airfoil in an airstream, it is convenient to describe the surface shape in polar coordinates (r, 6). On the following page, you will find the coordinates of several points on the surface of a Clark Y-14 airfoil. Write a MATLAB program to do the following: Store the airfoil shape (in polar coordinates) to variable(s). Convert the points to Cartesian coordinates (x,y). Generate a plot of these (x,y) points o de both markers and lines on the plot. o Label the axes appropriately. Be sure to include the units. o Your plot should be in a different figure window than the plot from Problem 4.2.Explanation / Answer
enter the values of theta with space in between...for example.
theta = [ 357.6 358.5 ]
enter the values of r with space in between .. for example
r= [ 29.13 27.62 ]
use the function [x,y] = pol2cart(theta,r) to convert .... for example...
[x,y] = pol2cart(theta,r);
use plot function to plot the cartesian points... example...
plot(x, y), xlabel('x in cm'), ylabel('Y in cm'), title('cARTESIAN POINTS'),
grid on, axis equal
Note:
The figure 4.2 is not given. If the data is in excel or any format that can be copied, then I can write the program. but here the data is given in image format. I had given the required function with example. Hope it will help you in writing the MATLAB code.
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