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AIRFOIL PROFILE12A 9.00% (rg12a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: AIRFOIL PROFILE12A 9.00% (rg12a-il)
Reynolds number: 1,000,000
Max Cl/Cd: 96.02 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rg12a-il-1000000.txt
Download as CSV file: xf-rg12a-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AIRFOIL PROFILE12A 9.00%                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4930   0.08801   0.08638  -0.0253   1.0000   0.0096
  -9.250  -0.4982   0.08248   0.08088  -0.0277   1.0000   0.0096
  -9.000  -0.5022   0.07814   0.07656  -0.0296   1.0000   0.0096
  -8.750  -0.5091   0.07333   0.07179  -0.0320   1.0000   0.0096
  -8.500  -0.5248   0.06691   0.06539  -0.0371   1.0000   0.0096
  -8.250  -0.5448   0.06175   0.06020  -0.0385   1.0000   0.0096
  -8.000  -0.5567   0.05600   0.05436  -0.0391   1.0000   0.0096
  -7.750  -0.5673   0.05057   0.04880  -0.0382   1.0000   0.0096
  -7.500  -0.5774   0.04555   0.04358  -0.0363   1.0000   0.0096
  -6.250  -0.4791   0.01919   0.01502  -0.0455   0.9881   0.0101
  -6.000  -0.4501   0.01586   0.01137  -0.0462   0.9865   0.0083
  -5.750  -0.4189   0.01337   0.00852  -0.0469   0.9851   0.0077
  -5.500  -0.3855   0.01205   0.00704  -0.0482   0.9840   0.0076
  -5.250  -0.3543   0.01118   0.00607  -0.0490   0.9818   0.0079
  -5.000  -0.3252   0.01052   0.00534  -0.0493   0.9780   0.0085
  -4.750  -0.2922   0.00996   0.00472  -0.0505   0.9755   0.0092
  -4.500  -0.2579   0.00940   0.00408  -0.0519   0.9735   0.0100
  -4.250  -0.2228   0.00875   0.00336  -0.0536   0.9718   0.0114
  -4.000  -0.1864   0.00839   0.00298  -0.0555   0.9706   0.0133
  -3.750  -0.1598   0.00799   0.00255  -0.0551   0.9644   0.0175
  -3.500  -0.1269   0.00747   0.00218  -0.0562   0.9608   0.0483
  -3.250  -0.0927   0.00711   0.00194  -0.0577   0.9576   0.0809
  -3.000  -0.0649   0.00675   0.00174  -0.0578   0.9494   0.1247
  -2.750  -0.0312   0.00630   0.00154  -0.0592   0.9436   0.1934
  -2.500  -0.0020   0.00582   0.00135  -0.0598   0.9330   0.2893
  -2.250   0.0274   0.00523   0.00118  -0.0604   0.9208   0.4226
  -2.000   0.0555   0.00474   0.00104  -0.0607   0.9057   0.5474
  -1.750   0.0819   0.00436   0.00099  -0.0604   0.8884   0.6717
  -1.500   0.1090   0.00433   0.00097  -0.0601   0.8687   0.7130
  -1.250   0.1359   0.00435   0.00095  -0.0596   0.8475   0.7380
  -1.000   0.1623   0.00441   0.00095  -0.0591   0.8251   0.7607
  -0.750   0.1887   0.00449   0.00094  -0.0587   0.8020   0.7731
  -0.500   0.2149   0.00457   0.00094  -0.0582   0.7776   0.7837
  -0.250   0.2410   0.00466   0.00095  -0.0577   0.7530   0.7935
   0.000   0.2673   0.00477   0.00096  -0.0572   0.7290   0.8028
   0.250   0.2934   0.00486   0.00099  -0.0567   0.7057   0.8111
   0.500   0.3198   0.00497   0.00102  -0.0563   0.6828   0.8188
   0.750   0.3460   0.00508   0.00106  -0.0559   0.6604   0.8265
   1.000   0.3724   0.00518   0.00109  -0.0555   0.6371   0.8341
   1.250   0.3987   0.00529   0.00115  -0.0551   0.6147   0.8418
   1.500   0.4247   0.00540   0.00120  -0.0547   0.5919   0.8499
   1.750   0.4511   0.00553   0.00126  -0.0543   0.5685   0.8590
   2.000   0.4767   0.00565   0.00133  -0.0538   0.5448   0.8667
   2.250   0.5030   0.00580   0.00141  -0.0535   0.5197   0.8733
   2.500   0.5288   0.00593   0.00148  -0.0530   0.4934   0.8787
   2.750   0.5551   0.00609   0.00156  -0.0527   0.4675   0.8843
   3.000   0.5810   0.00625   0.00165  -0.0524   0.4413   0.8899
   3.250   0.6065   0.00643   0.00177  -0.0519   0.4137   0.8963
   3.500   0.6318   0.00665   0.00189  -0.0515   0.3808   0.9031
   3.750   0.6568   0.00684   0.00202  -0.0509   0.3542   0.9107
   4.000   0.6807   0.00711   0.00217  -0.0502   0.3169   0.9196
   4.250   0.7037   0.00741   0.00235  -0.0493   0.2772   0.9309
   4.500   0.7261   0.00766   0.00251  -0.0482   0.2446   0.9454
   4.750   0.7499   0.00793   0.00269  -0.0474   0.2143   0.9653
   5.000   0.7813   0.00833   0.00294  -0.0485   0.1744   0.9880
   5.250   0.8087   0.00877   0.00321  -0.0488   0.1406   1.0000
   5.500   0.8338   0.00917   0.00349  -0.0485   0.1131   1.0000
   5.750   0.8583   0.00962   0.00380  -0.0481   0.0861   1.0000
   6.000   0.8824   0.01011   0.00415  -0.0477   0.0600   1.0000
   6.250   0.9050   0.01076   0.00463  -0.0470   0.0306   1.0000
   6.500   0.9288   0.01128   0.00510  -0.0463   0.0192   1.0000
   6.750   0.9530   0.01174   0.00556  -0.0458   0.0164   1.0000
   7.000   0.9762   0.01235   0.00626  -0.0449   0.0144   1.0000
   7.250   1.0006   0.01275   0.00671  -0.0444   0.0139   1.0000
   7.500   1.0247   0.01318   0.00719  -0.0439   0.0132   1.0000
   7.750   1.0480   0.01368   0.00776  -0.0432   0.0124   1.0000
   8.000   1.0708   0.01422   0.00837  -0.0425   0.0117   1.0000
   8.250   1.0927   0.01484   0.00903  -0.0416   0.0108   1.0000
   8.500   1.1103   0.01593   0.01024  -0.0400   0.0099   1.0000
   8.750   1.1264   0.01715   0.01159  -0.0383   0.0094   1.0000
   9.000   1.1492   0.01759   0.01209  -0.0376   0.0091   1.0000
   9.250   1.1703   0.01820   0.01278  -0.0367   0.0087   1.0000
   9.500   1.1907   0.01885   0.01351  -0.0357   0.0082   1.0000
   9.750   1.2108   0.01949   0.01420  -0.0347   0.0077   1.0000
  10.000   1.2301   0.02015   0.01492  -0.0336   0.0072   1.0000
  10.250   1.2481   0.02090   0.01571  -0.0324   0.0068   1.0000
  10.500   1.2475   0.02358   0.01862  -0.0286   0.0061   1.0000
  10.750   1.2667   0.02404   0.01914  -0.0275   0.0059   1.0000
  11.000   1.2809   0.02487   0.02008  -0.0257   0.0058   1.0000
  11.250   1.2921   0.02570   0.02101  -0.0235   0.0055   1.0000
  11.500   1.3018   0.02658   0.02200  -0.0211   0.0052   1.0000
  11.750   1.3086   0.02771   0.02323  -0.0184   0.0050   1.0000
  12.000   1.3164   0.02872   0.02434  -0.0162   0.0048   1.0000
  12.250   1.3195   0.03014   0.02588  -0.0136   0.0047   1.0000
  12.500   1.3223   0.03163   0.02749  -0.0114   0.0046   1.0000
  12.750   1.3277   0.03292   0.02885  -0.0097   0.0044   1.0000
  13.000   1.3304   0.03455   0.03057  -0.0082   0.0043   1.0000
  13.250   1.3336   0.03621   0.03230  -0.0070   0.0041   1.0000
  13.500   1.3233   0.03949   0.03575  -0.0057   0.0041   1.0000
  13.750   1.3124   0.04313   0.03956  -0.0054   0.0040   1.0000
  14.000   1.2956   0.04793   0.04454  -0.0060   0.0039   1.0000
  14.250   1.2801   0.05313   0.04993  -0.0075   0.0039   1.0000
  14.500   1.2606   0.05941   0.05640  -0.0101   0.0039   1.0000
  14.750   1.2380   0.06682   0.06401  -0.0138   0.0038   1.0000
  15.000   1.2313   0.07199   0.06929  -0.0167   0.0039   1.0000
  15.250   1.2069   0.08074   0.07822  -0.0218   0.0038   1.0000
  15.500   1.1855   0.08949   0.08712  -0.0270   0.0038   1.0000
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