The boundary layer module works best in the Reynolds number regime between 100'000 and 20'000'000. The results of the boundary layer module are also used to correct lift and moment, if separation occurs. Additionally, a blending to separated, flat plate coefficients is performed for very high angles of attack. How to use this WEB Page Input To simplify the input, you can enter a small number of parameters only. The airfoil has to be specified through coordinates which circle once around the airfoil.
All angles are with respect to the x-axis.
Your e-mail adress is used for troubleshooting and support only. The results are intended for personal use only. The results page presents the velocity distributions for all specified angles of attack and plots for lift coefficient over drag coefficient as well as lift coefficient versus angle of attack. You can also receive the polar data in PEF format and the velocity distribution in text format for further usage. Fill in the appropriate data into the form below and push the Analyse It button.