Does FLUENT predict Shock Wave location?

abhi.gajare · July 31, 2016, 16:04

Hi everyone!

I am working on my thesis project, related to reduction of drag in a transonic flow case over a NACA0012 airfoil. I am already late for my project so seriously need some help.

Does FLUENT predict the shock wave location by itself for a given flow condition (& BCs)?? I read that the transition point can somehow be fixed. If so, how is it done? Plz help with detailed description if possible.

Thank you in advance.

mattlevins · August 1, 2016, 12:19

Cant you just plot contours or pressure vs. X position and see where there are discontinuity in the plot

abhi.gajare · August 22, 2016, 14:48

Hello,

Update: I managed to calculate the shock-wave position, though for a 2D aerofoil, following instructions in this tutorial,

https://confluence.cornell.edu/displ...ow+Over+a+Wing

I used flow parameters such as AOA, Mach Number and Reynolds Number as given in a report of NASA, based on experiment results (Ref: C.D.Harris). But my simulation results (x vs Cp plot) did not match those given in the report. The shock-wave location was more upstream in my results for Mach numbers 0.75 & 0.8 (those are the only two I tried). Also the lower surface maximum Cp was significantly higher (in my simulation) than actual report values.

Kindly advice on what should I do now.

Thanks.

July 31, 2016, 16:04	Does FLUENT predict Shock Wave location?	#1
abhi.gajare New Member Abhishek Gajare Join Date: May 2016 Posts: 15 Rep Power: 10	Hi everyone! I am working on my thesis project, related to reduction of drag in a transonic flow case over a NACA0012 airfoil. I am already late for my project so seriously need some help. Does FLUENT predict the shock wave location by itself for a given flow condition (& BCs)?? I read that the transition point can somehow be fixed. If so, how is it done? Plz help with detailed description if possible. Thank you in advance.

August 22, 2016, 14:48	Update: Calculated shock-wave location, but it ain't right	#3
abhi.gajare New Member Abhishek Gajare Join Date: May 2016 Posts: 15 Rep Power: 10	Hello, Update: I managed to calculate the shock-wave position, though for a 2D aerofoil, following instructions in this tutorial, https://confluence.cornell.edu/displ...ow+Over+a+Wing I used flow parameters such as AOA, Mach Number and Reynolds Number as given in a report of NASA, based on experiment results (Ref: C.D.Harris). But my simulation results (x vs Cp plot) did not match those given in the report. The shock-wave location was more upstream in my results for Mach numbers 0.75 & 0.8 (those are the only two I tried). Also the lower surface maximum Cp was significantly higher (in my simulation) than actual report values. Kindly advice on what should I do now. Thanks. Dronzer likes this.

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August 1, 2016, 12:19		#2
mattlevins New Member Matt Levins Join Date: Nov 2014 Posts: 17 Rep Power: 11	Cant you just plot contours or pressure vs. X position and see where there are discontinuity in the plot