|
[Sponsors] |
February 9, 2012, 13:40 |
Modified NACA 4 and 5 series
|
#1 |
New Member
Tom
Join Date: Jan 2012
Posts: 11
Rep Power: 14 |
Does anyone know how to compute the coefficients for the thickness distribution equations for NACA 4 and 5 series equations? There is an explanation of how on this site:
http://www.pdas.com/naca456thick4mcalc.html But I still cannot figure out how to calculate them. I want to make my own code for generating the geometry which I can then use to test the foils in fluent. I do not want to just use other generators or codes because I need to make extensive modifications to the foil shapes and see how it affects performance. Thanks, Tom |
|
|
|
Similar Threads | ||||
Thread | Thread Starter | Forum | Replies | Last Post |
NACA 4 and 5 digit modified eqations | Tom A | Main CFD Forum | 3 | February 9, 2012 11:12 |
Mismatched NACA profiles | xTamx420 | Main CFD Forum | 0 | July 7, 2011 10:11 |
Symmetric NACA Airfoil Lift and Drag Data | jrider22 | Main CFD Forum | 3 | April 15, 2010 04:59 |
Ansys CFX Vs. NACA Summary Report. Mismatch Result | Santiago Orrego. | CFX | 3 | February 5, 2007 12:05 |
Naca 6 series | Ceylan kesenek | Main CFD Forum | 1 | October 19, 2001 02:51 |