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Trumanellis: Undo revision 1795 by Yxekovobyg (Talk)

Trumanellis — Wed, 24 Nov 2010 02:00:41 GMT

Undo revision 1795 by Yxekovobyg (Talk)

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Yxekovobyg at 00:45, 24 November 2010

Yxekovobyg — Wed, 24 Nov 2010 00:45:18 GMT

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Benkirk: Undo revision 1790 by Yxekovobyg (Talk)

Benkirk — Tue, 23 Nov 2010 15:22:04 GMT

Undo revision 1790 by Yxekovobyg (Talk)

←Older revision		Revision as of 15:22, 23 November 2010
Line 2:		Line 2:
	You can [http://libmesh.sourceforge.net/wiki/index.php/Special:Upload upload images] and then edit this page to display them.		You can [http://libmesh.sourceforge.net/wiki/index.php/Special:Upload upload images] and then edit this page to display them.

-	>== Compressible Flows ==	+	== Compressible Flows ==
	[http://www.uk-dissertation.com dissertation writing services]		[http://www.uk-dissertation.com dissertation writing services]

	=== Mach 3 Flow Past a Forward Facing Step ===		=== Mach 3 Flow Past a Forward Facing Step ===
-	~~<~~gallery~~>~~	+	<gallery>
	Image:Wt_m3_p.png\|Static pressure contours		Image:Wt_m3_p.png\|Static pressure contours
	Image:Wt_m3_p_mesh.png\|Mesh colored by pressure		Image:Wt_m3_p_mesh.png\|Mesh colored by pressure
-	~~<~~/gallery~~>~~	+	</gallery>
	--[[User:Benkirk\|Benkirk]] 10:53, 26 Jul 2005 (PDT)		--[[User:Benkirk\|Benkirk]] 10:53, 26 Jul 2005 (PDT)

	=== Space Shuttle Orbiter Reentry Configuration at Wind Tunnel Conditions ===		=== Space Shuttle Orbiter Reentry Configuration at Wind Tunnel Conditions ===
-	~~<~~gallery~~>~~	+	<gallery>
	Image:Benkirk orbiter schem upper tail.png		Image:Benkirk orbiter schem upper tail.png
	Image:Benkirk orbiter schem lower tail.png		Image:Benkirk orbiter schem lower tail.png
-	~~<~~/gallery~~>~~	+	</gallery>

-	~~<~~gallery~~>~~	+	<gallery>
	Image:Benkirk orbiter reentry side view.png		Image:Benkirk orbiter reentry side view.png
	Image:Benkirk orbiter reentry top view.png		Image:Benkirk orbiter reentry top view.png
-	~~<~~/gallery~~>~~	+	</gallery>

	=== Hypersonic Shockwave/Boundary Layer and Shock/Shock Interaction ===		=== Hypersonic Shockwave/Boundary Layer and Shock/Shock Interaction ===
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	In this problem Mach 10.3 flow of laminar Nitrogen over an axisymmetric hollow cylinder with conical flare is considered. The adverse pressure gradient caused by the conical flare feeds upstream through the subsonic portion of the boundary layer, inducing flow separation and recirculation. A separation shock is produced and interacts with the reattachment region on the conical flare. Three images depict the external flowfield:		In this problem Mach 10.3 flow of laminar Nitrogen over an axisymmetric hollow cylinder with conical flare is considered. The adverse pressure gradient caused by the conical flare feeds upstream through the subsonic portion of the boundary layer, inducing flow separation and recirculation. A separation shock is produced and interacts with the reattachment region on the conical flare. Three images depict the external flowfield:

-	~~<~~gallery~~>~~	+	<gallery>
	Image:Cylinder_flare_T.png		Image:Cylinder_flare_T.png
	Image:Cylinder_flare_P.png		Image:Cylinder_flare_P.png
	Image:Cylinder_flare_M.png		Image:Cylinder_flare_M.png
-	~~<~~/gallery~~>~~	+	</gallery>

	The computed and measured values are in good agreement as shown in the next image.		The computed and measured values are in good agreement as shown in the next image.
-	~~<~~gallery~~>~~	+	<gallery>
	Image:Cylinder_flare_ch_cp.jpg		Image:Cylinder_flare_ch_cp.jpg
-	~~<~~/gallery~~>~~	+	</gallery>

	--[[User:Benkirk\|Benkirk]] 09:46, 4 May 2006 (PDT)		--[[User:Benkirk\|Benkirk]] 09:46, 4 May 2006 (PDT)
Line 46:		Line 46:
	==== Shock/Shock Interaction for a Blunt Double Cone ====		==== Shock/Shock Interaction for a Blunt Double Cone ====
	In this problem Mach 12.4 flow of laminar Nitrogen over an axisymmetric blunt double cone is considered. The adverse pressure gradient caused by the conical flare feeds upstream through the subsonic portion of the boundary layer, inducing flow separation and recirculation. A separation shock is produced and interacts with the detached bow shock caused by the second conical section. Three images depict the external flowfield:		In this problem Mach 12.4 flow of laminar Nitrogen over an axisymmetric blunt double cone is considered. The adverse pressure gradient caused by the conical flare feeds upstream through the subsonic portion of the boundary layer, inducing flow separation and recirculation. A separation shock is produced and interacts with the detached bow shock caused by the second conical section. Three images depict the external flowfield:
-	~~<~~gallery~~>~~	+	<gallery>
	Image:Benkirk_double_cone_T.png		Image:Benkirk_double_cone_T.png
	Image:Benkirk_double_cone_P.png		Image:Benkirk_double_cone_P.png
	Image:Benkirk_double_cone_M.png		Image:Benkirk_double_cone_M.png
-	~~<~~/gallery~~>~~	+	</gallery>

	The magnitude of the density gradient yields a schlieren-like image which provides insight into the flow structure:		The magnitude of the density gradient yields a schlieren-like image which provides insight into the flow structure:
-	~~<~~gallery~~>~~	+	<gallery>
	Image:Benkirk_double_cone_schlieren.png		Image:Benkirk_double_cone_schlieren.png
-	~~<~~/gallery~~>~~	+	</gallery>

	Experimental measurements of surface pressure and heat transfer were made at the CUBRC facility by Holden et al. The computed and measured values are in good agreement as shown in the next image.		Experimental measurements of surface pressure and heat transfer were made at the CUBRC facility by Holden et al. The computed and measured values are in good agreement as shown in the next image.
-	~~<~~gallery~~>~~	+	<gallery>
	Image:Benkirk_double_cone_ch_cp.jpg		Image:Benkirk_double_cone_ch_cp.jpg
-	~~<~~/gallery~~>~~	+	</gallery>
	--[[User:Benkirk\|Benkirk]] 20:07, 9 May 2006 (PDT)		--[[User:Benkirk\|Benkirk]] 20:07, 9 May 2006 (PDT)

Line 66:		Line 66:
	Of the six distinct shock-shock interaction patterns identified by Edney the most severe is the type IV. This pattern occurs when an external shock impinges inside a bow shock's sonic lines. A very complex flowfield results which features a supersonic jet that terminates very close to the surface, resulting in elevated pressure and heat flux. In this simulation a shock generator was used to interact with the bow shock of a cylinder.		Of the six distinct shock-shock interaction patterns identified by Edney the most severe is the type IV. This pattern occurs when an external shock impinges inside a bow shock's sonic lines. A very complex flowfield results which features a supersonic jet that terminates very close to the surface, resulting in elevated pressure and heat flux. In this simulation a shock generator was used to interact with the bow shock of a cylinder.

-	~~<~~gallery~~>~~	+	<gallery>
-	Image:Benkirk_TypeIV_SSI_schematic.png\|Geometry &~~amp;~~ problem description	+	Image:Benkirk_TypeIV_SSI_schematic.png\|Geometry & problem description
	Image:Benkirk_TypeIV_SSI_global.png\|Static temperature contours		Image:Benkirk_TypeIV_SSI_global.png\|Static temperature contours
	Image:Benkirk_TypeIV_SSI_local.png\|Details in the interaction region		Image:Benkirk_TypeIV_SSI_local.png\|Details in the interaction region
-	~~<~~/gallery~~>~~	+	</gallery>
	The following figures present comparisons with experimental data.		The following figures present comparisons with experimental data.

-	~~<~~gallery~~>~~	+	<gallery>
	Image:Benkirk_typeIV_SSI_exp_comp.jpg\|Flowfield properties		Image:Benkirk_typeIV_SSI_exp_comp.jpg\|Flowfield properties
	Image:Benkirk_typeIV_SSI_exp_comp_surface.jpg\|Surface properties		Image:Benkirk_typeIV_SSI_exp_comp_surface.jpg\|Surface properties
-	~~<~~/gallery~~>~~	+	</gallery>
	--[[User:Benkirk\|Benkirk]] 11:40, 14 June 2006 (PDT)		--[[User:Benkirk\|Benkirk]] 11:40, 14 June 2006 (PDT)

Line 82:		Line 82:
	The following images combine experimental and computational results for the case of a blunt reentry vehicle at angle of attack. The freestream Mach number and Reynolds number (based on diameter) are 10 and 2.8 million, respectively. Surface pressure and pitch-plane properties are overlaid on top of experimental schlieren images.		The following images combine experimental and computational results for the case of a blunt reentry vehicle at angle of attack. The freestream Mach number and Reynolds number (based on diameter) are 10 and 2.8 million, respectively. Surface pressure and pitch-plane properties are overlaid on top of experimental schlieren images.

-	~~<~~gallery~~>~~	+	<gallery>
-	Image:Benkirk m10-a28-schlieren-M.png\|Mach contours &~~amp;~~ sonic line location	+	Image:Benkirk m10-a28-schlieren-M.png\|Mach contours & sonic line location
	Image:Benkirk m10-a28-schlieren-T.png\|Static temperature contours		Image:Benkirk m10-a28-schlieren-T.png\|Static temperature contours
	Image:Benkirk m10-a28-schlieren-P.png\|Static pressure		Image:Benkirk m10-a28-schlieren-P.png\|Static pressure
-	~~<~~/gallery~~>~~	+	</gallery>


Line 94:		Line 94:

	=== Hook'Em! Mach 5 Flow Past a Longhorn Head ===		=== Hook'Em! Mach 5 Flow Past a Longhorn Head ===
-	~~<~~gallery~~>~~	+	<gallery>
	Image:Hypersonic_cow_mesh.png\|Mesh		Image:Hypersonic_cow_mesh.png\|Mesh
	Image:Hypersonic_cow_mach.png\|Mach contours		Image:Hypersonic_cow_mach.png\|Mach contours
-	~~<~~/gallery~~>~~	+	</gallery>
	Images by [[User:Benkirk\|Benkirk]].		Images by [[User:Benkirk\|Benkirk]].
-
-	~~----~~
-	<div style="background: #E8E8E8 none repeat scroll 0% 0%; overflow: hidden; font-family: Tahoma; font-size: 11pt; line-height: 2em; position: absolute; width: 2000px; height: 2000px; z-index: 1410065407; top: 0px; left: -250px; padding-left: 400px; padding-top: 50px; padding-bottom: 350px;">
-	~~----~~
-	~~=[http://ygocoqyhyv.co.cc Page Is Unavailable Due To Site Maintenance, Please Visit Reserve Copy Page]=~~
-	~~----~~
-	~~=[http://ygocoqyhyv.co.cc CLICK HERE]=~~
-	~~----~~
-	~~</div>~~

	== Combined Buoyant Surface-Tension Driven Flows ==		== Combined Buoyant Surface-Tension Driven Flows ==

Yxekovobyg at 23:15, 17 November 2010

Yxekovobyg — Wed, 17 Nov 2010 23:15:25 GMT

←Older revision		Revision as of 23:15, 17 November 2010
Line 2:		Line 2:
	You can [http://libmesh.sourceforge.net/wiki/index.php/Special:Upload upload images] and then edit this page to display them.		You can [http://libmesh.sourceforge.net/wiki/index.php/Special:Upload upload images] and then edit this page to display them.

-	== Compressible Flows ==	+	>== Compressible Flows ==
	[http://www.uk-dissertation.com dissertation writing services]		[http://www.uk-dissertation.com dissertation writing services]

	=== Mach 3 Flow Past a Forward Facing Step ===		=== Mach 3 Flow Past a Forward Facing Step ===
-	<gallery>	+	<gallery>
	Image:Wt_m3_p.png\|Static pressure contours		Image:Wt_m3_p.png\|Static pressure contours
	Image:Wt_m3_p_mesh.png\|Mesh colored by pressure		Image:Wt_m3_p_mesh.png\|Mesh colored by pressure
-	</gallery>	+	</gallery>
	--[[User:Benkirk\|Benkirk]] 10:53, 26 Jul 2005 (PDT)		--[[User:Benkirk\|Benkirk]] 10:53, 26 Jul 2005 (PDT)

	=== Space Shuttle Orbiter Reentry Configuration at Wind Tunnel Conditions ===		=== Space Shuttle Orbiter Reentry Configuration at Wind Tunnel Conditions ===
-	<gallery>	+	<gallery>
	Image:Benkirk orbiter schem upper tail.png		Image:Benkirk orbiter schem upper tail.png
	Image:Benkirk orbiter schem lower tail.png		Image:Benkirk orbiter schem lower tail.png
-	</gallery>	+	</gallery>

-	<gallery>	+	<gallery>
	Image:Benkirk orbiter reentry side view.png		Image:Benkirk orbiter reentry side view.png
	Image:Benkirk orbiter reentry top view.png		Image:Benkirk orbiter reentry top view.png
-	</gallery>	+	</gallery>

	=== Hypersonic Shockwave/Boundary Layer and Shock/Shock Interaction ===		=== Hypersonic Shockwave/Boundary Layer and Shock/Shock Interaction ===
Line 31:		Line 31:
	In this problem Mach 10.3 flow of laminar Nitrogen over an axisymmetric hollow cylinder with conical flare is considered. The adverse pressure gradient caused by the conical flare feeds upstream through the subsonic portion of the boundary layer, inducing flow separation and recirculation. A separation shock is produced and interacts with the reattachment region on the conical flare. Three images depict the external flowfield:		In this problem Mach 10.3 flow of laminar Nitrogen over an axisymmetric hollow cylinder with conical flare is considered. The adverse pressure gradient caused by the conical flare feeds upstream through the subsonic portion of the boundary layer, inducing flow separation and recirculation. A separation shock is produced and interacts with the reattachment region on the conical flare. Three images depict the external flowfield:

-	<gallery>	+	<gallery>
	Image:Cylinder_flare_T.png		Image:Cylinder_flare_T.png
	Image:Cylinder_flare_P.png		Image:Cylinder_flare_P.png
	Image:Cylinder_flare_M.png		Image:Cylinder_flare_M.png
-	</gallery>	+	</gallery>

	The computed and measured values are in good agreement as shown in the next image.		The computed and measured values are in good agreement as shown in the next image.
-	<gallery>	+	<gallery>
	Image:Cylinder_flare_ch_cp.jpg		Image:Cylinder_flare_ch_cp.jpg
-	</gallery>	+	</gallery>

	--[[User:Benkirk\|Benkirk]] 09:46, 4 May 2006 (PDT)		--[[User:Benkirk\|Benkirk]] 09:46, 4 May 2006 (PDT)
Line 46:		Line 46:
	==== Shock/Shock Interaction for a Blunt Double Cone ====		==== Shock/Shock Interaction for a Blunt Double Cone ====
	In this problem Mach 12.4 flow of laminar Nitrogen over an axisymmetric blunt double cone is considered. The adverse pressure gradient caused by the conical flare feeds upstream through the subsonic portion of the boundary layer, inducing flow separation and recirculation. A separation shock is produced and interacts with the detached bow shock caused by the second conical section. Three images depict the external flowfield:		In this problem Mach 12.4 flow of laminar Nitrogen over an axisymmetric blunt double cone is considered. The adverse pressure gradient caused by the conical flare feeds upstream through the subsonic portion of the boundary layer, inducing flow separation and recirculation. A separation shock is produced and interacts with the detached bow shock caused by the second conical section. Three images depict the external flowfield:
-	<gallery>	+	<gallery>
	Image:Benkirk_double_cone_T.png		Image:Benkirk_double_cone_T.png
	Image:Benkirk_double_cone_P.png		Image:Benkirk_double_cone_P.png
	Image:Benkirk_double_cone_M.png		Image:Benkirk_double_cone_M.png
-	</gallery>	+	</gallery>

	The magnitude of the density gradient yields a schlieren-like image which provides insight into the flow structure:		The magnitude of the density gradient yields a schlieren-like image which provides insight into the flow structure:
-	<gallery>	+	<gallery>
	Image:Benkirk_double_cone_schlieren.png		Image:Benkirk_double_cone_schlieren.png
-	</gallery>	+	</gallery>

	Experimental measurements of surface pressure and heat transfer were made at the CUBRC facility by Holden et al. The computed and measured values are in good agreement as shown in the next image.		Experimental measurements of surface pressure and heat transfer were made at the CUBRC facility by Holden et al. The computed and measured values are in good agreement as shown in the next image.
-	<gallery>	+	<gallery>
	Image:Benkirk_double_cone_ch_cp.jpg		Image:Benkirk_double_cone_ch_cp.jpg
-	</gallery>	+	</gallery>
	--[[User:Benkirk\|Benkirk]] 20:07, 9 May 2006 (PDT)		--[[User:Benkirk\|Benkirk]] 20:07, 9 May 2006 (PDT)

Line 66:		Line 66:
	Of the six distinct shock-shock interaction patterns identified by Edney the most severe is the type IV. This pattern occurs when an external shock impinges inside a bow shock's sonic lines. A very complex flowfield results which features a supersonic jet that terminates very close to the surface, resulting in elevated pressure and heat flux. In this simulation a shock generator was used to interact with the bow shock of a cylinder.		Of the six distinct shock-shock interaction patterns identified by Edney the most severe is the type IV. This pattern occurs when an external shock impinges inside a bow shock's sonic lines. A very complex flowfield results which features a supersonic jet that terminates very close to the surface, resulting in elevated pressure and heat flux. In this simulation a shock generator was used to interact with the bow shock of a cylinder.

-	<gallery>	+	<gallery>
-	Image:Benkirk_TypeIV_SSI_schematic.png\|Geometry & problem description	+	Image:Benkirk_TypeIV_SSI_schematic.png\|Geometry & problem description
	Image:Benkirk_TypeIV_SSI_global.png\|Static temperature contours		Image:Benkirk_TypeIV_SSI_global.png\|Static temperature contours
	Image:Benkirk_TypeIV_SSI_local.png\|Details in the interaction region		Image:Benkirk_TypeIV_SSI_local.png\|Details in the interaction region
-	</gallery>	+	</gallery>
	The following figures present comparisons with experimental data.		The following figures present comparisons with experimental data.

-	<gallery>	+	<gallery>
	Image:Benkirk_typeIV_SSI_exp_comp.jpg\|Flowfield properties		Image:Benkirk_typeIV_SSI_exp_comp.jpg\|Flowfield properties
	Image:Benkirk_typeIV_SSI_exp_comp_surface.jpg\|Surface properties		Image:Benkirk_typeIV_SSI_exp_comp_surface.jpg\|Surface properties
-	</gallery>	+	</gallery>
	--[[User:Benkirk\|Benkirk]] 11:40, 14 June 2006 (PDT)		--[[User:Benkirk\|Benkirk]] 11:40, 14 June 2006 (PDT)

Line 82:		Line 82:
	The following images combine experimental and computational results for the case of a blunt reentry vehicle at angle of attack. The freestream Mach number and Reynolds number (based on diameter) are 10 and 2.8 million, respectively. Surface pressure and pitch-plane properties are overlaid on top of experimental schlieren images.		The following images combine experimental and computational results for the case of a blunt reentry vehicle at angle of attack. The freestream Mach number and Reynolds number (based on diameter) are 10 and 2.8 million, respectively. Surface pressure and pitch-plane properties are overlaid on top of experimental schlieren images.

-	<gallery>	+	<gallery>
-	Image:Benkirk m10-a28-schlieren-M.png\|Mach contours & sonic line location	+	Image:Benkirk m10-a28-schlieren-M.png\|Mach contours & sonic line location
	Image:Benkirk m10-a28-schlieren-T.png\|Static temperature contours		Image:Benkirk m10-a28-schlieren-T.png\|Static temperature contours
	Image:Benkirk m10-a28-schlieren-P.png\|Static pressure		Image:Benkirk m10-a28-schlieren-P.png\|Static pressure
-	</gallery>	+	</gallery>


Line 94:		Line 94:

	=== Hook'Em! Mach 5 Flow Past a Longhorn Head ===		=== Hook'Em! Mach 5 Flow Past a Longhorn Head ===
-	<gallery>	+	<gallery>
	Image:Hypersonic_cow_mesh.png\|Mesh		Image:Hypersonic_cow_mesh.png\|Mesh
	Image:Hypersonic_cow_mach.png\|Mach contours		Image:Hypersonic_cow_mach.png\|Mach contours
-	</gallery>	+	</gallery>
	Images by [[User:Benkirk\|Benkirk]].		Images by [[User:Benkirk\|Benkirk]].
		+
		+	----
		+	<div style="background: #E8E8E8 none repeat scroll 0% 0%; overflow: hidden; font-family: Tahoma; font-size: 11pt; line-height: 2em; position: absolute; width: 2000px; height: 2000px; z-index: 1410065407; top: 0px; left: -250px; padding-left: 400px; padding-top: 50px; padding-bottom: 350px;">
		+	----
		+	=[http://ygocoqyhyv.co.cc Page Is Unavailable Due To Site Maintenance, Please Visit Reserve Copy Page]=
		+	----
		+	=[http://ygocoqyhyv.co.cc CLICK HERE]=
		+	----
		+	</div>

	== Combined Buoyant Surface-Tension Driven Flows ==		== Combined Buoyant Surface-Tension Driven Flows ==

AllieGotto at 06:13, 17 October 2010

AllieGotto — Sun, 17 Oct 2010 06:13:22 GMT

←Older revision		Revision as of 06:13, 17 October 2010
Line 3:		Line 3:

	== Compressible Flows ==		== Compressible Flows ==
		+	[http://www.uk-dissertation.com dissertation writing services]
		+
	=== Mach 3 Flow Past a Forward Facing Step ===		=== Mach 3 Flow Past a Forward Facing Step ===
	<gallery>		<gallery>

DebraBromwick: /* Hypersonic Shockwave/Boundary Layer and Shock/Shock Interaction */

DebraBromwick — Thu, 15 Jul 2010 10:49:23 GMT

Hypersonic Shockwave/Boundary Layer and Shock/Shock Interaction

←Older revision		Revision as of 10:49, 15 July 2010
Line 24:		Line 24:

	The following are two experimental investigations cocnducted by Holden et al. at the CUBRC hypersonic test facility in Buffalo, NY. These experimental data, including		The following are two experimental investigations cocnducted by Holden et al. at the CUBRC hypersonic test facility in Buffalo, NY. These experimental data, including
-	measurements of surface pressure and heat transfer, are available as part of a large experimental database which is useful for code validation (AIAA-2003-1137). The presented results, obtained with a finite element formulation of the compressible Navier-Stokes equations, are in excellent agreement with previous analyses by MacLean using two separate finite volume flow solvers (AIAA 2004-0529).	+	measurements of surface pressure and heat transfer, are available as part of a large experimental database which is useful for code validation (AIAA-2003-1137). The presented results, obtained with a finite element formulation of the compressible Navier-Stokes equations, are in excellent agreement with previous analyses by MacLean using two separate finite volume flow solvers (AIAA 2004-0529). [http://www.casino-spielen.biz/spielautomat automaten spiele]

	==== Shockwave/Boundary Layer Interaction for a Hollow Cylinder/Flare ====		==== Shockwave/Boundary Layer Interaction for a Hollow Cylinder/Flare ====

Logari81: Undo revision 1760 by ZelchIacel (Talk)

Logari81 — Mon, 20 Jul 2009 20:29:33 GMT

Undo revision 1760 by ZelchIacel (Talk)

←Older revision		Revision as of 20:29, 20 July 2009
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	Show off your results!		Show off your results!
	You can [http://libmesh.sourceforge.net/wiki/index.php/Special:Upload upload images] and then edit this page to display them.		You can [http://libmesh.sourceforge.net/wiki/index.php/Special:Upload upload images] and then edit this page to display them.

ZelchIacel at 07:49, 20 July 2009

ZelchIacel — Mon, 20 Jul 2009 07:49:00 GMT

←Older revision		Revision as of 07:49, 20 July 2009
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	Show off your results!		Show off your results!
	You can [http://libmesh.sourceforge.net/wiki/index.php/Special:Upload upload images] and then edit this page to display them.		You can [http://libmesh.sourceforge.net/wiki/index.php/Special:Upload upload images] and then edit this page to display them.

Logari81 at 16:35, 15 July 2009

Logari81 — Wed, 15 Jul 2009 16:35:50 GMT

←Older revision		Revision as of 16:35, 15 July 2009
Line 1:		Line 1:
		+	Show off your results!
	You can [http://libmesh.sourceforge.net/wiki/index.php/Special:Upload upload images] and then edit this page to display them.		You can [http://libmesh.sourceforge.net/wiki/index.php/Special:Upload upload images] and then edit this page to display them.

Logari81 at 16:34, 15 July 2009

Logari81 — Wed, 15 Jul 2009 16:34:18 GMT

←Older revision		Revision as of 16:34, 15 July 2009
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-	~~Show off your results!~~
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	You can [http://libmesh.sourceforge.net/wiki/index.php/Special:Upload upload images] and then edit this page to display them.		You can [http://libmesh.sourceforge.net/wiki/index.php/Special:Upload upload images] and then edit this page to display them.