not getting Mach no 1 at throat -- CFD Online Discussion Forums

November 18, 2013, 05:37	not getting Mach no 1 at throat	#1
mehul447 New Member mehul chhowala Join Date: Nov 2013 Posts: 1 Rep Power: 0	hi guys i am using fluent for supersonic nozzle design.. but some how i am get mach number is one at throat section, i used k-e model,segregated solver,boundary condition is given mass flow rate inlet and pressure outlet,in result i get constant density throughout nozzle.please help me.my outlet pressure is 0.80 bar and mass flow rate inlet is 11.11 kg/s.

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 Forum Rules

Similar Threads
Thread	Thread Starter	Forum	Replies	Last Post
Averae Mach Number	yunusrulz	Main CFD Forum	0	June 27, 2013 08:00
How obtain a Mach number value from a case run with Xifoam solver??	lfgmarc	OpenFOAM Programming & Development	0	June 15, 2011 03:00
Fully Expanded Jet Mach Number.	oe_jet	Main CFD Forum	0	June 28, 2010 11:40
Strong oscillation at transonic mach number	martingariepy	FLUENT	2	May 12, 2009 11:40
Inviscid Drag at subsonic, subcritical Mach #	Axel Rohde	Main CFD Forum	1	November 19, 2001 12:19

All times are GMT -4. The time now is 19:15.