Recent content by kronecker77

Hi, Sure, i will message u back in a day or two. At present i m struggling with a boundary layer velocity profile problem. I have everything. Only problem is in visualizing how to plot the velocity profiles. The problem is about using blasius solution to plot the velocity profiles of u and v...

Hi, I just realized the flaw in my code. Thank you all for your help.

True. M on a learning curve at the moment. Ur advices are helpful.

Thank you for that advice. I will implement that.

s_x and s_y are the coordinates of the center of the circle and r is the radius of the circle in a complex plane which i have to transform to an airfoil using joukowski transform. s is he distance of the center of the circle from the origin. The imaginary part is there because this is a complex...

[code] clear all close all clc v_inf = input(' Enter the Speed [m/s]: '); v = v_inf/v_inf; alpha = input(' enter angle of attack [deg]: '); alpha = alpha*pi/180; s_x = input(' Circle Origin, X_0 [m]: '); s_y = input(' Circle Origin, Y_0 [m]: '); s = s_x + 1i*s_y; r = input(' Radius [m]...

I m stuck on how to write the loops for the points on airfoil where i have to plot the pressuer values

Thank u for ur help. I m having problems in plotting the graphs.

I m stuck somewhere as i m not that good in programming. I know the physics behind that but i m not able to write a computer program for that.

I am given a project to transform an airfoil from a cylinder using joukowski transform. The cylinder is in zeta plane and the airfoil is in z plane. I did the plotting and i got the airfoil shape using matlab. but i want to know how to plot the pressure distribution over the airfoil. The...