Help me for solving this integral
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hello iam trying to solve this integral

so i write the script in matlab as follows :
syms x
v = 45.12 ; %normal velocity
r = 418.87 ; %angular velocity at 4000 rpm
ratio = 91 ; %max lift/drag coeff. @ alpha = 10 degree
chord = 0.2 ; %chord length
row = 1.225 ; %air density
l = (0.5*ratio*chord*row*((v^2)+(r*x-u*x)^2)); %lift func.
c = (r*x-0.5*u*x)/((v^2)+(r*x-0.5*u*x)^2)^0.5; %cos func.
t = (l*c); %total lift func.
a = int(t , 0.15 , 0.45);
display('lift: '), disp(double(a));
Solution
t =
(31887*x*((2136042788971*x^2)/4000000 + 19962065511551291219/879609302220800))/(100*((1016780769*x^2)/10000 + 4476803209587641/2199023255552)^(1/2))
lift: 2.0311e+004
the problem is the solution is not logic because this equation is function in u so u is unknown must appear in result .
could any one tell me how to solve it please ?
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