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June 23, 2020, 20:39 |
NASA CRM wing simulation in SU2
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#1 |
New Member
Ranjan
Join Date: Apr 2014
Posts: 29
Rep Power: 12 |
Hello
I am trying to simulate inviscid flow-field around the NASA CRM wing. Even though my dimensions are correct, I get extremely high values for CL and CD ( almost double ) when compared to the design conditions of AOA ~ 2.34 degrees. I have tried both manual and automatic values for A_ref ( by setting A_ref zero), the manual entry for A_ref being 191.82 m^2. I have also tried multiple mesh resolutions, varying from 3-9 Million. Any suggestions ? Thanks in advance |
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June 23, 2020, 22:33 |
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#2 | |
New Member
Join Date: Jul 2019
Posts: 5
Rep Power: 7 |
Quote:
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June 23, 2020, 23:07 |
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#3 |
New Member
Ranjan
Join Date: Apr 2014
Posts: 29
Rep Power: 12 |
I am not sure what you mean by " why is the AOA in the config file ? "
The flow angle of attack is always defined in the config file. The config file is attached as a .txt file with my post. Thank you |
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August 24, 2020, 16:13 |
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#4 |
New Member
Join Date: Jun 2020
Posts: 14
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What is the axis of lift in your mesh? Is it z-axis?
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September 3, 2020, 15:58 |
Resolved
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#5 |
New Member
Ranjan
Join Date: Apr 2014
Posts: 29
Rep Power: 12 |
I figured out the problem. The axis orientation and the configuration in general were correct. However, Euler flow assumption especially for the CRM wing at design condition leads to spurious ( over-predicted ) aerodynamic characteristics. While one might expect to predict the pressure forces and hence the lift distribution to a reasonable accuracy, the CRM geometry encapsulated viscous effects such as shock-induced boundary layer separation , a phenomenon absent in Euler assumption.
Upon switching to RANS and a computational domain with appropriate near-wall resolution ( yPlus ~ 1 ), the flow characteristics computed were reasonable when compared to other numerical experiments. Thank you all ! |
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Tags |
crm wing, euler, su2 |
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