Recent content by Thusithatck

Hello, Can some explain to me how to calculate the power coefficient of a vertical axis wind turbine. If you explain the steps invloved would be great or any external file location where I could refer. I have below information 1) Lift Coefficient. 2) Drag Coefficient. 3) Angle of...

[SIZE="2"]I have plotted a lift curve of a NACA 643-418 airfoil section which has a flat region in the lift curve approximately from 11 degrees to 16 degrees. Beyond 16 degrees it completely stalls. Can some explain to me the reason behind this flat region in the lift curve. The experiment...

I'm trying to write a MATLAB code but I get an error message which I'm not sure why. The code is follows as, %%%%% Code %%%%% for i = 1:1:v; for j = 1:0.1:a TSR(i,j)=wR/i; end end %%%%% Code %%%%% Here 'a' is taken as...

I was told to vary the number of panels around the airfoil to get a good agreement with the experimental data. Where the panels in XFoil are similar to those cells in Fluent. Free transition, and input parameters (Re, and M) are correct. Therefore the initial conditions would be valid. Only...

Just to confirm, my wind tunnel experimental Reynolds number is 380,000. So when I specify the Reynolds number in XFoil using the "Re" command, do I need to enter it as 1107872 (Reynolds number based on a UNIT chord) which will be 380,000 when multiplied by 0.343m (actual chord length). Or...

Can someone explain to me how XFoil calculates the Reynolds Number for computational analysis. I have the XFoil manual which explains the method used in calculating the Reynolds Number. But what I don't understand is that it says that the "Reynolds Number is defined with the freestream velocity...

The document seems to contain computational data not experimental data. Thanks anyway.

Does anybody have any experimental data on flat back airfoils. I would like to know the experimental data, experimental setup and initial flow parameters etc. In case if you find it from a report I would be glad if you can give some information regarding the report, such as author, report name...

I have used 43 panels as I tried to replicate experimental data. 43 panels gave me the closest fit to the experimental data. I did tried using 200 panels, but it over predicted massively.

I'm trying to validate some experimental data on a NACA 643-418 wing section from XFoil. Below are some basis data, Number of panels around the airfoil - 43 Mach number - 0.0487 Reynold number - 1107872 Velocity - 16.67 (not important) During the analysis I have set the upper surface...