|
[Sponsors] |
Problems with generated results of 3D wing analysis |
|
LinkBack | Thread Tools | Search this Thread | Display Modes |
March 12, 2010, 10:37 |
Problems with generated results of 3D wing analysis
|
#1 |
New Member
Chong Shao ming
Join Date: Mar 2010
Posts: 1
Rep Power: 0 |
Hi all,
I am using Fluent to analyse a typical 3D wing problem under low Re. However, the CL which was obtained is way too high in region of 3.7 for AoA of 4! (selected results from force report) Force vector: (0.06976 0.997564 0) pressure total pressure total force force coefficient coefficient n n -------------- -------------- 2.2806709 2.2830547 3.7235443 3.7274363 -------------- -------------- -------------- -------------- 2.2806709 2.2830547 3.7235443 3.7274363 Could anyone help verify if the parameters used are suitable and correct? Fluent (grid checks and scaling have been carried out correctly) Solver: Pressure-based Materials: constant density and viscosity Viscous Model: Spalart-Allmaras (at default values) Operating Conditions: Op pressure = 101325 Pa Boundary Conditions: (kindly refer to attached file) Inlet-velocity inlet Outlet-pressure outlet Kindly point out any possible loopholes which i might have in the meshing as well. (FYI airfoil used is GEMINI, c=0.171m, b=1.2) Thanks in advance! |
|
|
|
Similar Threads | ||||
Thread | Thread Starter | Forum | Replies | Last Post |
3D Wing Analysis | Ed | FLUENT | 5 | April 13, 2019 13:07 |
multi wing element - negative coefficient of drag? | Zweeper | FLUENT | 10 | March 11, 2010 12:20 |
Problems with repeating results | Lee | Siemens | 4 | May 26, 2006 03:39 |
problems viewing results with VNC | Ralf Schmidt | FLUENT | 3 | February 1, 2006 01:40 |
Boundary layer on a wing | Mark | FLUENT | 0 | August 18, 2004 20:24 |