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S4061-096-84 (s4061-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S4061-096-84 (s4061-il)
Reynolds number: 100,000
Max Cl/Cd: 59.74 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4061-il-100000.txt
Download as CSV file: xf-s4061-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4061-096-84                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3165   0.10104   0.09633  -0.0338   1.0000   0.0888
  -8.500  -0.3306   0.09998   0.09541  -0.0384   1.0000   0.0912
  -8.250  -0.3492   0.09906   0.09467  -0.0408   1.0000   0.0917
  -8.000  -0.3111   0.09233   0.08784  -0.0361   1.0000   0.0964
  -7.750  -0.3127   0.09031   0.08591  -0.0352   1.0000   0.1003
  -7.500  -0.3285   0.08940   0.08513  -0.0328   1.0000   0.1020
  -7.250  -0.3538   0.08938   0.08526  -0.0284   1.0000   0.1026
  -7.000  -0.3791   0.08917   0.08516  -0.0244   1.0000   0.1030
  -6.750  -0.3967   0.08806   0.08414  -0.0225   1.0000   0.1033
  -6.500  -0.4240   0.08700   0.08317  -0.0277   1.0000   0.1054
  -6.250  -0.4228   0.08268   0.07888  -0.0307   0.9982   0.1069
  -6.000  -0.4009   0.07977   0.07598  -0.0259   0.9950   0.1111
  -5.750  -0.3678   0.07274   0.06879  -0.0443   0.9853   0.1215
  -5.500  -0.3468   0.06961   0.06570  -0.0427   0.9800   0.1249
  -5.250  -0.3110   0.06361   0.05950  -0.0554   0.9725   0.1369
  -5.000  -0.2893   0.06060   0.05650  -0.0558   0.9654   0.1411
  -4.750  -0.2347   0.04306   0.03770  -0.0764   0.9594   0.0801
  -4.500  -0.2020   0.03579   0.02952  -0.0797   0.9530   0.0629
  -4.250  -0.1651   0.03164   0.02476  -0.0827   0.9476   0.0607
  -4.000  -0.1246   0.02884   0.02119  -0.0854   0.9430   0.0635
  -3.750  -0.0934   0.02667   0.01849  -0.0862   0.9357   0.0659
  -3.500  -0.0522   0.02472   0.01638  -0.0887   0.9313   0.0716
  -3.250  -0.0216   0.02351   0.01501  -0.0892   0.9241   0.0824
  -3.000   0.0165   0.02230   0.01381  -0.0910   0.9183   0.1119
  -2.750   0.0541   0.02162   0.01320  -0.0930   0.9127   0.1666
  -2.500   0.0846   0.02104   0.01281  -0.0938   0.9049   0.2146
  -2.250   0.1280   0.02032   0.01230  -0.0966   0.9008   0.2814
  -2.000   0.1503   0.01998   0.01221  -0.0958   0.8914   0.3447
  -1.750   0.1878   0.01920   0.01197  -0.0974   0.8866   0.4675
  -1.500   0.2060   0.01863   0.01212  -0.0951   0.8775   0.6428
  -1.250   0.2618   0.01774   0.01167  -0.0988   0.8738   1.0000
  -1.000   0.2913   0.01797   0.01162  -0.0991   0.8657   1.0000
  -0.750   0.3237   0.01809   0.01150  -0.0998   0.8583   1.0000
  -0.500   0.3496   0.01837   0.01160  -0.0996   0.8495   1.0000
  -0.250   0.3824   0.01845   0.01150  -0.1001   0.8427   1.0000
   0.000   0.4062   0.01878   0.01169  -0.0995   0.8332   1.0000
   0.250   0.4393   0.01879   0.01156  -0.0999   0.8270   1.0000
   0.500   0.4618   0.01916   0.01183  -0.0991   0.8168   1.0000
   0.750   0.4950   0.01910   0.01166  -0.0993   0.8112   1.0000
   1.000   0.5168   0.01949   0.01199  -0.0984   0.8005   1.0000
   1.250   0.5500   0.01936   0.01177  -0.0985   0.7953   1.0000
   1.500   0.5717   0.01975   0.01213  -0.0975   0.7841   1.0000
   1.750   0.5976   0.01994   0.01228  -0.0969   0.7753   1.0000
   2.000   0.6268   0.01990   0.01219  -0.0965   0.7676   1.0000
   2.250   0.6507   0.02017   0.01244  -0.0956   0.7571   1.0000
   2.500   0.6823   0.01989   0.01213  -0.0952   0.7509   1.0000
   2.750   0.7058   0.02012   0.01237  -0.0942   0.7393   1.0000
   3.000   0.7316   0.02019   0.01244  -0.0934   0.7290   1.0000
   3.250   0.7621   0.01986   0.01207  -0.0927   0.7214   1.0000
   3.500   0.7864   0.02000   0.01227  -0.0917   0.7094   1.0000
   3.750   0.8123   0.02002   0.01231  -0.0908   0.6983   1.0000
   4.000   0.8421   0.01970   0.01197  -0.0900   0.6896   1.0000
   4.250   0.8683   0.01964   0.01197  -0.0891   0.6777   1.0000
   4.500   0.8938   0.01965   0.01202  -0.0882   0.6648   1.0000
   4.750   0.9198   0.01959   0.01201  -0.0872   0.6519   1.0000
   5.000   0.9463   0.01950   0.01195  -0.0863   0.6387   1.0000
   5.250   0.9729   0.01939   0.01190  -0.0854   0.6248   1.0000
   5.500   0.9992   0.01928   0.01183  -0.0844   0.6097   1.0000
   5.750   1.0253   0.01918   0.01176  -0.0834   0.5933   1.0000
   6.000   1.0514   0.01907   0.01170  -0.0823   0.5759   1.0000
   6.250   1.0776   0.01897   0.01158  -0.0813   0.5574   1.0000
   6.500   1.1003   0.01908   0.01178  -0.0800   0.5345   1.0000
   6.750   1.1244   0.01912   0.01181  -0.0788   0.5111   1.0000
   7.000   1.1470   0.01927   0.01196  -0.0774   0.4848   1.0000
   7.250   1.1679   0.01955   0.01222  -0.0760   0.4553   1.0000
   7.500   1.1872   0.01998   0.01261  -0.0744   0.4230   1.0000
   7.750   1.2050   0.02055   0.01315  -0.0726   0.3887   1.0000
   8.000   1.2215   0.02128   0.01375  -0.0708   0.3548   1.0000
   8.250   1.2366   0.02218   0.01449  -0.0690   0.3222   1.0000
   8.500   1.2504   0.02319   0.01541  -0.0671   0.2906   1.0000
   8.750   1.2632   0.02434   0.01644  -0.0651   0.2614   1.0000
   9.000   1.2746   0.02560   0.01758  -0.0630   0.2344   1.0000
   9.250   1.2845   0.02693   0.01883  -0.0608   0.2088   1.0000
   9.500   1.2915   0.02828   0.02015  -0.0584   0.1839   1.0000
   9.750   1.2949   0.02968   0.02145  -0.0556   0.1621   1.0000
  10.000   1.2956   0.03109   0.02285  -0.0526   0.1422   1.0000
  10.250   1.2963   0.03281   0.02445  -0.0500   0.1251   1.0000
  10.500   1.2976   0.03476   0.02639  -0.0476   0.1083   1.0000
  10.750   1.2989   0.03692   0.02854  -0.0454   0.0931   1.0000
  11.000   1.3011   0.03927   0.03089  -0.0434   0.0804   1.0000
  11.250   1.3058   0.04168   0.03327  -0.0418   0.0705   1.0000
  11.500   1.3191   0.04423   0.03565  -0.0405   0.0622   1.0000
  11.750   1.3311   0.04665   0.03839  -0.0390   0.0576   1.0000
  12.000   1.3438   0.04895   0.04074  -0.0379   0.0535   1.0000
  12.250   1.3604   0.05210   0.04401  -0.0371   0.0500   1.0000
  12.500   1.3641   0.05499   0.04724  -0.0357   0.0481   1.0000
  12.750   1.3679   0.05829   0.05085  -0.0344   0.0467   1.0000
  13.000   1.3681   0.06183   0.05470  -0.0333   0.0458   1.0000
  13.250   1.3639   0.06563   0.05879  -0.0324   0.0452   1.0000
  13.500   1.3553   0.06981   0.06327  -0.0317   0.0448   1.0000
  13.750   1.3416   0.07446   0.06823  -0.0316   0.0447   1.0000
  14.000   1.3229   0.07972   0.07379  -0.0321   0.0448   1.0000
  14.250   1.2991   0.08579   0.08017  -0.0335   0.0451   1.0000
  14.500   1.2716   0.09273   0.08742  -0.0361   0.0455   1.0000
  14.750   1.2411   0.10076   0.09571  -0.0400   0.0461   1.0000
  15.000   1.2088   0.11000   0.10519  -0.0454   0.0469   1.0000
  15.250   1.1746   0.12085   0.11625  -0.0524   0.0479   1.0000
  15.500   1.1398   0.13339   0.12892  -0.0609   0.0491   1.0000
  15.750   1.1108   0.14620   0.14179  -0.0691   0.0503   1.0000
  16.000   1.0943   0.15673   0.15232  -0.0751   0.0512   1.0000
  16.250   1.0412   0.18703   0.18244  -0.0927   0.0632   1.0000
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