J.Divahar (j.divahar@yahoo.com) Manual
Files Folders and constitution After extracting the downloaded zip file the extracted folder “Potential_Flow_simulator” will contain the following files and folders.
Airfoil_Coordinate_Files FOLDER There are total of 1550 Airfoils’ Coordinates files are classified under respective folders in the folder “Airfoil_Coordinate_Files\Airfoil_Bank”. You can copy some of the airfoil data files into the “Current_Files” folder, which need to listed in the selection option under Choose Airfoil Co-ordinate file sub menu. The Classified folders are the following, CLARK Airfoils ( 11 - Data Files ) EPPLER Airfoils ( 207 - Data Files ) GOE Airfoils ( 396 - Data Files ) NACA Airfoils ( 181 - Data Files ) RAE and RAF ( 29 - Data Files ) WORTMANN FX Aifoils (117 - Data Files ) Other Airfoils ( 609 - Data Files )
Arbitrary_Body_Coordinate_Files FOLDER All the coordinate files for the arbitrary shaped bodies reside here. When the File menu is clicked this folder will be read for the list of arbitrary body files and listed in the menu under “Choose Arbitrary Body Co-ordinate file” sub menu.
Captured_images FOLDER Here is where all the captured images (.jpg) will be stored after automated naming.
Help_files FOLDER All the help files including the one that you are reading now will be kept in this folder. Along the help files (.htm), their respective supporting folders will also be here.
Results_files FOLDER The exported Ms.Excel files will be stored here in this folder after automated naming.
alltools.mat This is a MAT file containing the images that are to be mapped on to the tool bar buttons, as matrices. During the creation of all the buttons these images will be mapped on to the respective buttons after loading this MAT file. Potential_Flow_Simulator.fig
This is the MATLAB GUI figure (.fig) that contains all the features and information of the GUI. When the main code “Potential_Flow_Simulator.m” is executed this FIG file will be opened and shown as GUI. Potential_Flow_Simulator.m The MAIN CODE.
Usage When you click the File menu the simulator will dynamically read the folder “Current_Files” and list all the DAT files in that folder as the selection options under Choose Airfoil Co-ordinate file sub menu and also read the folder Arbitrary_Body_Coordinate_Files and list the DAT files under “Choose Arbitrary Body Co-ordinate file” submenu. There are total of 1550 Airfoils’ Coordinates files are classified under few folders in the folder “Airfoil_Coordinate_Files\Airfoil_Bank”. You can copy some of the airfoil data files into the “Current_Files” folder, which need to listed in the selection menu. All the 1550 Airfoils are checked to be compatible with the constraints to be read as input !!! The Options menu will be directing you to customization in view, run options and exporting the data and images. In the tool bar, the tool tip ( small pop up message - when the pointer is kept over the button) will be guiding for various views options like pan, zoom, panzoom and data cursor. In Options -> Export Settings, it can be chosen whether the cL alpha data or the Cp distribution is to be exported as excel file and similarly for capturing the image also there are options like whether or not to Include Inputs, Title & Axis. There is also a movie tool that will animate the vector plot flow over the body. Many other things are made so as to be self explanatory.
Creating Custom Coordinate Data Input file One can create his own coordinate file of any desired arbitrary shape. The constraints for the coordinate files are ● Files should be “.dat” files ● Files should contain in the first line Name of Airfoil or Body ( Not Greater than 25 alpha numeric characters) and the remaining all lines should have only numerical data of x and y coordinates in 2 columns delimited by tab or space. (Note: The Airfoil data file name will be displayed in the selection menu but the name will be displayed in the text Aifoil or Body text box. ● The over all length of the body should be 1 (one) and maximum thickness/length (t/c) can only be 2 for better performance. ● In case of Airfoil, the coordinates should start at the trailing edge (1,y1) in the anticlockwise (note flow is from left to right) and end at the same point or near to it (1,yn) . Mid point (y) of the first point and the SECOND last point will be made as trailing edge if the airfoil does not have an unique Trailing Edge.
● The coordinate data sites should be distinct ( i.e. single valued at a particular x location - no discontinuity ). In other words, the x– coordinate should not be repeated consecutively.
Note: * In animated vector plot the arrow will not indicate the relative magnitude whereas in the static vector plot the size of the arrows will indicate the relative magnitude of the velocity. * Vector plot will be generated only for one angle of attack per run, which will be selected before running the simulation. But the cL-Alpha Curve and Cp distribution will be computed for the range of angles of attack. * One can see the Cp distribution for range of angles of attack (-16 to 16 degree) just by changing the AOA in the drop down Pop up menu. *While exporting the data as Excel file or during capturing the image please wait till the process gets over. * Only limited no. of Coordinate data files can be listed in the selection menu.
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