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1、Tutorial for XFoilInstalling XFoil-Copy the downloaded file to the directory where you want to install XFoil and run it.Running Xfoil-XFoil is executed by going to the directory where it was installed and typing% xfoilLoading an Airfoil-The load or NACA command can used to load an airfoil into XFoil
2、. In this tutorial we will be using a NACA 2412 airfoil. To load this airfoil typeXFOIL c NACA 2412Notice that XFoil will return some of the specifications for the airfoil, including the location and magnitude of the maximum thickness, maximum camber, and other parameters.Cleaning the Airfoil Geomet
3、ry-It is a good idea to ensure that the airfoil loaded does not contain panels that create very sharp edges. The PANE command in XFoil smoothes out the airfoil geometry.XFOIL c paneNOTE: The commands are not case sensitiveThe OPER Sub-Level-TypeXFOIL c OPERThis will produce the prompt.OPERi cType a
4、“? to see a list of available commands and a brief description of their use. This works on any level of XFoil.In the OPER level this is what you will see after typing “?” Return to Top Level ! Redo last ALFA,CLI,CL,ASEQ,CSEQ,VELS Visc r Toggle Inviscid/Viscous mode .VPAR Change BL parameter(s) Re r
5、Change Reynolds number Mach r Change Mach number Type i Change type of Mach,Re variation with CL ITER Change viscous-solution iteration limit INIT Toggle BL initialization flag Alfa r Prescribe alpha CLI r Prescribe inviscid CL Cl r Prescribe CL ASeq rrr Prescribe a sequence of alphas CSeq rrr Presc
6、ribe a sequence of CLs SEQP Toggle polar/Cp(x) sequence plot display CINC Toggle minimum Cp inclusion in polar HINC Toggle hinge moment inclusion in polar Pacc i Toggle auto point accumulation to active polar PGET f Read new polar from save file PWRT i Write polar to save file PSUM Show summary of s
7、tored polars PLIS i List stored polar(s) PDEL i Delete stored polar PSOR i Sort stored polar PPlo ii. Plot stored polar(s) APlo ii. Plot stored airfoil(s) for each polar ASET i Copy stored airfoil into current airfoil PREM ir. Remove point(s) from stored polar PPAX Change polar plot axis limits RGET
8、 f Read new reference polar from file RDEL i Delete stored reference polar GRID Toggle Cp vs x grid overlay CREF Toggle reference Cp data overlay FREF Toggle reference CL,CD. data display CPx Plot Cp vs x CPV Plot airfoil with pressure vectors (gee wiz) .VPlo BL variable plots .ANNO Annotate current
9、 plot HARD Hardcopy current plot SIZE r Change plot-object size CPMI r Change minimum Cp axis annotation BL i Plot boundary layer velocity profiles BLC Plot boundary layer velocity profiles at cursor BLWT r Change velocity profile scale weight FMOM Calculate flap hinge moment and forces FNEW rr Set
10、new flap hinge point VELS rr Calculate velocity components at a point DUMP f Output Ue,Dstar,Theta,Cf vs s,x,y to file CPWR f Output x vs Cp to file CPMN Report minimum surface Cp NAME s Specify new airfoil name NINC Increment name version numberNotice that there are three columns, the first is the
11、command, the second one gives an indication of other inputs the command needs. An r means that the command expects a real number, an i means that the command expects an integer, an f means that the command expects a filename, and an s that the command expects a string. If the input is not typed afte
12、r the command XFoil will prompt the user.XFoil Under Inviscid Mode-Notice the “i” next to “.OPER” on the prompt. This indicates that XFoil is in inviscid mode. Type.OPERi c alfa 0XFoil will find the flow around the airfoil for the given angle of attack, in this case, 0. Notice that a window pops up
13、showing the pressure distribution, the section lift coefficient, the section moment coefficient, the angle of attack and the airfoil name.Figure 1. Cp Distribution at alpha = 0Type.OPERi c cl 0.7XFoil will find the angle of attack at which the current airfoil produces the section lift coefficient th
14、at has been input. Notice that XFoil once again plots the pressure distribution around the airfoil like it did previously.Figure 2. Pressure Distrubion at Cl = 0.6Viscous Mode-Type.OPERi c viscThis command will turn on the viscous mode. XFoil then prompts the user to input a Reynolds number. For this tutorial we will work with a low Reynolds number, type “3e6 at the prompt. Notice that a “v” will now appea
