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Subject: NACA0012 aerodynamic data at low Re#

Date: 09/10/99
Posted by: Youngwhe Park
E-mail: pyw(at)snu(dot)ac(dot)kr(no spam)
URL: http://

Message:

hello! i have took wind tunnel testing 2-D NACA0012 airfoil at 200,000 - 400,000 reynolds numbers. but i cannot get lift and drag data for validating my experiment setup. i have got some data in adelade universtiy web site, but this is not sufficient. anyone who knows the way to get these data, please tell me.. i will appreciate for your answer. have a good luck to everyone...

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