Airfoil Analysis - Revision history

Altadyna: /* Definitions */

2016-02-20T15:09:31Z

‎Definitions

2015-07-10T23:44:49Z

‎Analyzing the results

2015-07-10T23:43:24Z

‎Analyzing the results

2015-07-10T23:40:45Z

‎Analyzing the results

2015-07-10T23:28:17Z

‎Analyzing the results

2015-07-10T23:26:09Z

‎Analyzing the results

2015-07-10T23:24:56Z

‎Analyzing the results

2015-07-09T23:56:04Z

‎Analyzing the results

2015-07-09T23:55:35Z

‎Analyzing the results

2015-07-09T23:52:57Z

‎Analyzing the results

← Older revision		Revision as of 15:09, 20 February 2016
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		+	Click on the "Inlet/outlet" tab, then select "velo_in" to check the turbulence intensity. Use the default values if you do not wish to make a change.

	Next click on "OK" to accept and close this dialog. The Reynolds number for this analysis is 300,000.		Next click on "OK" to accept and close this dialog. The Reynolds number for this analysis is 300,000.

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 To plot the Cp against chord position, first click on the surface result file in the "Pipeline Browser". Then click on menu "Filters->Alphabetical->CellDataToPointData". Hit "Apply" in the "Properties" panel to convert surface cell data to point data. Then click on menu "Filters->Alphabetical->ScatterPlot". Hit "Apply" in the "Properties" panel to convert surface cell data to point data. An x-y chart is shown in the main view. Activate the "Display" panel, set "X Axis Data" to "Use Data Array->Points (0)". In the "Line Series", uncheck all except "Cp". Click on "Cp" there and set "Line Style" to "None" and "Marker Style" to "Cross".
-[[File:Sg6043d_Cp_scatter.png|400 px]]
+[[File:Sg6043d_scatter_plot.png|thumb|140 px]]
 [[Category:Tutorials]]

@@ Line 105: / Line 105: @@
 To plot the Cp against chord position, first click on the surface result file in the "Pipeline Browser". Then click on menu "Filters->Alphabetical->CellDataToPointData". Hit "Apply" in the "Properties" panel to convert surface cell data to point data. Then click on menu "Filters->Alphabetical->ScatterPlot". Hit "Apply" in the "Properties" panel to convert surface cell data to point data. An x-y chart is shown in the main view. Activate the "Display" panel, set "X Axis Data" to "Use Data Array->Points (0)". In the "Line Series", uncheck all except "Cp". Click on "Cp" there and set "Line Style" to "None" and "Marker Style" to "Cross".
 [[File:Sg6043d_Cp_scatter.png|400 px]]
 [[Category:Tutorials]]

← Older revision		Revision as of 23:40, 10 July 2015
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	[[File:Sg6043d_Cp_contour.png\|400 px]]		[[File:Sg6043d_Cp_contour.png\|400 px]]
		+
		+	To plot the Cp against chord position, first click on the surface result file in the "Pipeline Browser". Then click on menu "Filters->Alphabetical->CellDataToPointData". Hit "Apply" in the "Properties" panel to convert surface cell data to point data. Then click on menu "Filters->Alphabetical->ScatterPlot". Hit "Apply" in the "Properties" panel to convert surface cell data to point data. An x-y chart is shown in the main view. Activate the "Display" panel, set "X Axis Data" to "Use Data Array->Points (0)". In the "Line Series", uncheck all except "Cp". Click on "Cp" there and set "Line Style" to "None" and "Marker Style" to "Cross".
		+
		+	[[File:Sg6043d_Cp_scatter.png\|400 px]]

	[[Category:Tutorials]]		[[Category:Tutorials]]

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 =Analyzing the results=
-For airfoils, users are typically interested in the lift and drag. Open the force output file in Polaris Viewer or in a text editor, one can find the drag Fx=79.5 N/m, lift Fy=2881.1 N/m, the air density=1.293 kg/m^3 as reported by the solver, one can compute Cd=0.034, Cl=1.235 which match the results in [http://m-selig.ae.illinois.edu/uiuc_lsat/Low-Speed-Airfoil-Data-V3.pdf Summary of Low-Speed Airfoil Data].
+For airfoils, users are typically interested in the lift and drag. Open the force output file in Polaris Viewer or in a text editor, one can find the drag Fx=79.5 N/m, lift Fy=2881.1 N/m, the air density=1.293 kg/m^3 as reported by the solver, the characteristic velocity=60m/s, characteristic length=1m, one can compute Cd=0.034, Cl=1.235 which match the results in [http://m-selig.ae.illinois.edu/uiuc_lsat/Low-Speed-Airfoil-Data-V3.pdf Summary of Low-Speed Airfoil Data].
 <!-- does not work  7-9-2015

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 [[File:Sg6043d_mach.png|400 px]]
-One can plot isolines for 2d fluid results. First click on the fluid file in the "Pipeline Browser", then click on menu "Filters->Alphabetical->CellDataToPointData". Hit "Apply" in the "Properties" panel to convert fluid cell data to point data. Then click on the "Contour" button in the toolbar or in the "Filters" menu. Select "Cp" as the "Contour By" variable. Click on "New Range" in the "Properties" panel and set 21 intervals. Hit "Apply" in the "Properties" panel to see the isolines..
+One can plot isolines for 2d fluid results. First click on the fluid file in the "Pipeline Browser", then click on menu "Filters->Alphabetical->CellDataToPointData". Hit "Apply" in the "Properties" panel to convert fluid cell data to point data. Then click on the "Contour" button in the toolbar or in the "Filters" menu. Select "Cp" as the "Contour By" variable. Click on "New Range" in the "Properties" panel and set 21 intervals. Hit "Apply" in the "Properties" panel to see the isolines. The isolines initially are white. Users can color them by a variable.
 [[File:Sg6043d_Cp_contour.png|400 px]]
 [[Category:Tutorials]]

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 {{math|''f''(<var>x</var>) {{=}} <var>x</var><sup>2</sup>}}
 -->
 In Polaris Viewer, load surface result file and set the view mode to "Wireframe". Load the fluid result file and set the view mode to "Surface" and then pick "Mach number" as the display variable. Go to the last timestep. Zoom in to the airfoil and one can observe this plot.
 [[File:Sg6043d_mach.png|400 px]]
 [[Category:Tutorials]]