CFD Online Logo CFD Online URL
www.cfd-online.com
[Sponsors]
Home > Forums > General Forums > Main CFD Forum

supersonic flow over flat plate

Register Blogs Community New Posts Updated Threads Search

Reply
 
LinkBack Thread Tools Search this Thread Display Modes
Old   March 23, 2010, 02:43
Default supersonic flow over flat plate
  #1
Member
 
varun
Join Date: Apr 2009
Posts: 35
Rep Power: 17
varunjain89 is on a distinguished road
hello!

i have been writing C code to solve supersonic flow over flat plate, using finite difference method.

I'm using assuming steady state solution.

I'm using the boudary layer eqns, or reduced N-S eqns. I have been getting decent results for subsonic flow.

but for supersonic flow, i realized that boundary conditions cannot be fress stream conditions, so can anyone suggest what boundary conditions @ leading edge should i use..

thank you very much

varun jain
varunjain89 is offline   Reply With Quote

Old   March 23, 2010, 09:26
Default
  #2
agd
Senior Member
 
Join Date: Jul 2009
Posts: 357
Rep Power: 19
agd is on a distinguished road
You'll probably want to take a look at Riemann boundary conditions. These utilize the Riemann invariants based on the local state of the flow at the boundary.
agd is offline   Reply With Quote

Reply


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
Supersonic flow over flat plate Nikhil Main CFD Forum 6 May 20, 2013 13:48
incompressible, 2-D laminar flow over flat plate... varunjain89 Main CFD Forum 3 March 6, 2012 12:13
supersonic flow past flat plate shuo Main CFD Forum 0 July 28, 2007 20:47
PIV - transitional flat plate flows MC Main CFD Forum 0 July 4, 2007 09:21
Conjugate heat transfer for film-cooled flat plate Michele FLUENT 0 July 3, 2006 09:42


All times are GMT -4. The time now is 06:30.