* Extensive Help is also included for better utilization. Eventually, the airfoil is optimized by using MATLAB fmincon solvers, which are Sequential Quadratic Programming and Interior-Point Methods. Then, the aerodynamic characteristics of the airfoil are evaluated thanks to MATLAB-XFOIL interface. * Well Customization is made possible through the Options menu Firstly, the base airfoil, which is NACA4412, is generated by using MATLAB 1 and it is analyzed in XFOIL.
Even if the data files are added, removed or renamed when the simulator is open ( before running the simulation ), the simulator detects it and updates the list. c c d liu ta NACA 4 digit, 5 digit hay 6 series, ta c th s dng nhiu cch khc nhau.V d ly d liu t trang airfoiltools.
* The Menu lists the available data files very dynamically. * One can view the pressure distribution for range of angles attack dynamically and interactively * Total of 1550 Airfoils coordinates files are provided with the simulator ( All are checked for compatibility so that the simulator can read without any problem ). You can also generate your own coordinates file of any shape and associate with the simulator. * Total of 9 Arbitrary bodies coordinates files are included in the simulator as default. * Automatic name generation for exporting the data and capturing the images to avoid the confusions that are very common in any Scientific Computing. * Capture the images that are generated in the simulator (Profile and mesh details of the body, Vector plot, Cp distribution and cL - alpha Curve ) as. * Export the pressure distribution and the cL-Alpha data at various angles of attack as Ms.Excel file. * Compute and plot the cL Vs alpha Curve of the selected body. * Compute and plot the Pressure Distribution in terms of both Cp ( pressure coefficient ) and 1-Cp. * Compute and plot the Velocity Vector Plot of the flow past the selected body. With this simulator, we can do the following tasks, ● All of these are kept in an attractive and user friendly Graphical User Interface.This potential flow simulator simulates the flow past bodies of arbitrary shape including airfoils. of data files in the current folder is displayed. ● In the title bar of the Airfoil Analyzer's window, the no. ● Automatic focusing is done while viewing the leading edge circle and trailing edge cusp angle so that continuous and repeated zoom and pan operations are eliminated. ● Well Customization is made possible through the controls in "Properties Settings for Next Plot" and "Current View Options" tabs. ● Dynamically one can change the folder to be read, where the data files are residing just by clicking the "Change Airfoil Data Folder" button. ● Line style, Marker style, Line width and color of the next plot can be set through the "Properties Settings for Next Plot" tab. ● Total of 1550 Airfoils' coordinate files are provided under classified folders with the Airfoil Analyzer. ► Airfoils can be quickly plotted at just selection. ► For panel method analysis and other methods, aifoils can be examined for mesh details. ► Leading edge radius, trailing edge cusp angle, camber line distribution, maximum camber & its location, and maximum thickness & its location, which are the important technical features of airfoils, can be computed from the airfoil coordinate data files and plotted. ► Upto 3 airfoils can be ploted together in the plot area to compare the geometrical features and the similarities among them can be analyzed and explored. Airfoil Analyzer will be useful in the following the ways, This Airfoil Analyzer tool is mainly intended to be useful in analyzing and comparing the airfoils' geometrical features and in quick plotting of airfoils.