CFD Online Logo CFD Online URL
Home > Forums > Software User Forums > Siemens

Compressible flow - 2D NACA0012 Aerofoil Sim.

Register Blogs Members List Search Today's Posts Mark Forums Read

LinkBack Thread Tools Search this Thread Display Modes
Old   July 6, 2006, 06:11
Default Compressible flow - 2D NACA0012 Aerofoil Sim.
MSc Student
Posts: n/a
Hi Im simulating supersonic transonic and subsonic compressible flow over a 2D NACA0012 aerofoil and Im trying to learn how to do this using the star userguide and tutorial 6 the supersonic tutorial.

Im looking to do a viscous simulation solving the N-S equations over the domain.

Ive readied my mesh and set the boundary regions. Im at the stage of setting the fluid and material properties.Ive set the density to ideal f(T,P) to make the flow compressible. But I havent seen any documentation on what to set the viscosity. Ive also set the temperature calculation to be on. So the energy equation is solved as well as the momentum and continuity. If the temperature changes and is solved across the domain then wont viscosity be changing too? In this case I cant leave the viscosity constant and its not an invisicd simulation.. so what is the best option to choose for viscous compressible flow? Ill be using the k-epsilon turbulence model and the simulation will be steady state not transient. In using version 3.24 of star-cd

  Reply With Quote

Old   July 10, 2006, 06:51
Default Re: Compressible flow - 2D NACA0012 Aerofoil Sim.
Ankush Aggarwal
Posts: n/a
First make sure that you choose the Conservation of Stagnation Enthalpy in the temperature calculation options(as this is a compressible case) and then for viscosity you can find some table on the internet of viscosity agaionst the temperature....then you need to make a table and choose the user table in the options(i have never done that, refer to the user guide)
  Reply With Quote

Old   July 10, 2006, 08:55
Default Re: Compressible flow - 2D NACA0012 Aerofoil Sim.
MSc Student
Posts: n/a
Ive just looked up the conservation of stagnation enthalpy in the help section and it states that stagnation enthalpy condition is: used under adiabatic, inviscid flow conditions; assumes that the total enthalpy is constant and uniform throughout the model (see equation (1-18)). Supply the value of the (constant) stagnation temperature in the Stagnation Temp. box

This doesnt make sense to me as my flow is viscous.

The conservation of total enthalpy seems to be more applicable to my situation as it states in the help total enthalpy is applicable mainly to high-speed, compressible flows.

If I do need to choose stagnation enthalpy how do I calculate the constant stagnation temperature?
  Reply With Quote

Old   August 26, 2006, 01:32
Default Re: Compressible flow - 2D NACA0012 Aerofoil Sim.
Posts: n/a
  Reply With Quote


Thread Tools Search this Thread
Search this Thread:

Advanced Search
Display Modes

Posting Rules
You may not post new threads
You may not post replies
You may not post attachments
You may not edit your posts

BB code is On
Smilies are On
[IMG] code is On
HTML code is Off
Trackbacks are Off
Pingbacks are On
Refbacks are On

Similar Threads
Thread Thread Starter Forum Replies Last Post
Compressible Flow Around Aerofoil Vishal FLUENT 0 July 2, 2008 02:23
Simulation of transonic flow over NACA0012 airfoil MSc Student Siemens 2 August 9, 2006 13:49
Unsteady simulation on the flow around Naca0012 Peter Pan Zhang FLUENT 2 June 11, 2006 19:53
how to model a NACA0012 aerofoil in GAMBIT GOVINDARAJU L FLUENT 2 January 6, 2006 02:56
Simulating NACA0012 for inviscid flow. Stan Main CFD Forum 2 May 13, 2005 14:22

All times are GMT -4. The time now is 09:34.