|
[Sponsors] |
Validation of NACA 0012 against Nasa published; |
|
LinkBack | Thread Tools | Search this Thread | Display Modes |
November 10, 2015, 11:10 |
Validation of NACA 0012 against Nasa published;
|
#1 |
Senior Member
|
Dear Fluent Users;
http://turbmodels.larc.nasa.gov/naca0012_val.html Referring to this case I have shown link to I am sure every one has worked on it if you are interested in flow in aerospace. I am having a tough time not knowing how NASA got their Reynolds number as 6 million. The Reference Temp = 300K or 540 Rankine... Flow M = 0.15 ~ is roughlu 51.45 m/s Reference Chord Length = 1m; Mu or Kinematic viscocity of air at 300k ~= 1.57e-05 m2/s. And if so: Re = VL/(mu) = Therefore = (51.45 * 1)/(1.57e-05) = 3.28 million. Can some one express their views Regards Shereez |
|
November 25, 2017, 11:27 |
|
#3 |
New Member
Viral Patel
Join Date: Oct 2017
Posts: 1
Rep Power: 0 |
Did you get an answer in the end?
I changed my kinematic viscosity in FLUENT to reach a Reynolds number of 6million - but I'm not sure if this is correct. |
|
|
|
Similar Threads | ||||
Thread | Thread Starter | Forum | Replies | Last Post |
2D NACA 0012 Airfoil Validation Case (NASA) | jp3g12 | OpenFOAM Running, Solving & CFD | 24 | April 23, 2021 14:34 |
NACA 0012 2D validation | cfdseeker | CFX | 15 | December 30, 2014 15:42 |
NACA 0012 validation Drag problems | leo_NM | FLUENT | 7 | August 8, 2014 14:18 |
Naca 0012 validation, Cd value is too high. | Peter88 | OpenFOAM | 4 | January 21, 2014 16:10 |
2D NACA 0012 Airfoil Validation | nvtrieu | FLUENT | 0 | May 30, 2013 10:22 |