Help me for solving this integral
Show older comments
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 ?
Accepted Answer
More Answers (0)
Categories
Find more on Calculus in Help Center and File Exchange
Community Treasure Hunt
Find the treasures in MATLAB Central and discover how the community can help you!
Start Hunting!