|
[Sponsors] |
NACA 0012 Cl values (Lift) not dropping post-stall? |
|
LinkBack | Thread Tools | Search this Thread | Display Modes |
December 7, 2020, 12:55 |
NACA 0012 Cl values (Lift) not dropping post-stall?
|
#1 |
New Member
R St
Join Date: Dec 2020
Posts: 3
Rep Power: 5 |
Hi, I'm new to fluent, I am conducting a study comparing wind tunnel data of Cl, Cp to Fluent data. my Cl values are all good up until the stall angle. The Cl does not converge (even after 5,000 iterations), and keeps going up and AoA increases when the wind tunnel Cl drops after the stall. This is really frustrating as I want to do the rest of my analysis but can't because of these obviously incorrect values.
My classmates have managed to get the correct Cl values. I'm using K-Omega SST, Mesh Quality check was good, sensitivity check was good, approx 148k nodes used, Re approx 332k. I have attached some screenshots, I am at a loss as to what is wrong here. |
|
|
|
Similar Threads | ||||
Thread | Thread Starter | Forum | Replies | Last Post |
Low Reynolds NACA 0012 validation | 35matt215 | CFX | 9 | March 17, 2019 22:12 |
yPlus NACA 0012 Airfoil | badwalgurpreet | OpenFOAM Running, Solving & CFD | 7 | March 8, 2019 01:35 |
Lift and drag coefficients of the NACA 0018 | Volodymyr | CONVERGE | 4 | September 22, 2017 17:52 |
Oscillating residual, lift and drag values | aptahaney | Main CFD Forum | 0 | July 8, 2015 13:16 |
Lift and Drag Monitor Point Values Converging to Zero | Josh | CFX | 24 | May 9, 2011 10:38 |