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SD6080 (9.2%) (sd6080-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: SD6080 (9.2%) (sd6080-il)
Reynolds number: 1,000,000
Max Cl/Cd: 137.42 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd6080-il-1000000.txt
Download as CSV file: xf-sd6080-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD6080 (9.2%)                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3630   0.11013   0.10847  -0.0235   1.0000   0.0082
 -10.000  -0.3578   0.10682   0.10517  -0.0248   1.0000   0.0082
  -8.000  -0.3216   0.07677   0.07527  -0.0418   0.9789   0.0102
  -7.750  -0.3104   0.06752   0.06598  -0.0545   0.9463   0.0105
  -7.500  -0.3072   0.06307   0.06144  -0.0590   0.9165   0.0105
  -7.250  -0.3023   0.05931   0.05759  -0.0625   0.8963   0.0107
  -7.000  -0.2944   0.05520   0.05338  -0.0663   0.8798   0.0108
  -6.750  -0.2820   0.05206   0.05015  -0.0690   0.8665   0.0112
  -6.500  -0.2691   0.04733   0.04529  -0.0728   0.8541   0.0115
  -6.250  -0.2544   0.04198   0.03975  -0.0762   0.8426   0.0119
  -6.000  -0.2376   0.03511   0.03259  -0.0790   0.8322   0.0130
  -4.750  -0.1305   0.01376   0.00876  -0.0799   0.7892   0.0104
  -4.500  -0.1041   0.01248   0.00731  -0.0796   0.7814   0.0100
  -4.250  -0.0773   0.01129   0.00592  -0.0794   0.7730   0.0100
  -4.000  -0.0502   0.01056   0.00505  -0.0791   0.7652   0.0101
  -3.750  -0.0231   0.00976   0.00412  -0.0789   0.7571   0.0104
  -3.500   0.0039   0.00904   0.00330  -0.0787   0.7494   0.0113
  -3.250   0.0316   0.00871   0.00290  -0.0787   0.7414   0.0119
  -3.000   0.0596   0.00843   0.00256  -0.0786   0.7338   0.0126
  -2.750   0.0875   0.00819   0.00225  -0.0785   0.7260   0.0132
  -2.500   0.1157   0.00795   0.00195  -0.0785   0.7186   0.0143
  -2.250   0.1437   0.00773   0.00166  -0.0784   0.7111   0.0169
  -2.000   0.1718   0.00743   0.00142  -0.0784   0.7037   0.0355
  -1.750   0.1996   0.00719   0.00129  -0.0784   0.6964   0.0778
  -1.500   0.2276   0.00700   0.00120  -0.0785   0.6891   0.1176
  -1.250   0.2553   0.00676   0.00113  -0.0785   0.6818   0.1838
  -1.000   0.2831   0.00650   0.00109  -0.0787   0.6747   0.2637
  -0.750   0.3103   0.00617   0.00106  -0.0787   0.6673   0.3807
  -0.500   0.3378   0.00589   0.00105  -0.0788   0.6600   0.4858
  -0.250   0.3647   0.00562   0.00106  -0.0787   0.6523   0.6017
   0.000   0.3905   0.00526   0.00109  -0.0782   0.6446   0.7408
   0.250   0.4105   0.00486   0.00114  -0.0762   0.6370   0.9118
   0.500   0.4528   0.00478   0.00109  -0.0791   0.6287   1.0000
   0.750   0.4804   0.00486   0.00109  -0.0790   0.6209   1.0000
   1.000   0.5082   0.00491   0.00110  -0.0790   0.6125   1.0000
   1.250   0.5360   0.00499   0.00112  -0.0789   0.6042   1.0000
   1.500   0.5638   0.00506   0.00114  -0.0789   0.5953   1.0000
   1.750   0.5916   0.00513   0.00117  -0.0788   0.5862   1.0000
   2.000   0.6193   0.00523   0.00120  -0.0788   0.5768   1.0000
   2.250   0.6471   0.00530   0.00124  -0.0788   0.5668   1.0000
   2.500   0.6749   0.00539   0.00130  -0.0787   0.5568   1.0000
   2.750   0.7025   0.00549   0.00136  -0.0787   0.5464   1.0000
   3.000   0.7300   0.00561   0.00142  -0.0786   0.5347   1.0000
   3.250   0.7575   0.00572   0.00149  -0.0786   0.5221   1.0000
   3.500   0.7850   0.00584   0.00158  -0.0785   0.5089   1.0000
   3.750   0.8123   0.00598   0.00168  -0.0785   0.4947   1.0000
   4.000   0.8393   0.00614   0.00178  -0.0784   0.4785   1.0000
   4.250   0.8663   0.00632   0.00190  -0.0783   0.4615   1.0000
   4.500   0.8932   0.00650   0.00204  -0.0781   0.4431   1.0000
   4.750   0.9196   0.00673   0.00219  -0.0780   0.4216   1.0000
   5.000   0.9459   0.00697   0.00236  -0.0778   0.3990   1.0000
   5.250   0.9711   0.00733   0.00258  -0.0775   0.3655   1.0000
   5.500   0.9953   0.00780   0.00285  -0.0771   0.3221   1.0000
   5.750   1.0196   0.00826   0.00314  -0.0767   0.2847   1.0000
   6.000   1.0438   0.00872   0.00344  -0.0763   0.2511   1.0000
   6.500   1.0915   0.00967   0.00410  -0.0754   0.1906   1.0000
   6.750   1.1149   0.01018   0.00447  -0.0749   0.1617   1.0000
   7.000   1.1383   0.01066   0.00483  -0.0743   0.1378   1.0000
   7.250   1.1614   0.01116   0.00523  -0.0738   0.1148   1.0000
   7.500   1.1836   0.01174   0.00567  -0.0731   0.0906   1.0000
   7.750   1.2046   0.01241   0.00619  -0.0723   0.0652   1.0000
   8.000   1.2228   0.01334   0.00690  -0.0711   0.0340   1.0000
   8.250   1.2402   0.01432   0.00772  -0.0697   0.0137   1.0000
   8.500   1.2620   0.01482   0.00826  -0.0689   0.0119   1.0000
   8.750   1.2829   0.01539   0.00886  -0.0680   0.0108   1.0000
   9.000   1.3020   0.01609   0.00964  -0.0667   0.0098   1.0000
   9.250   1.3216   0.01670   0.01031  -0.0656   0.0094   1.0000
   9.500   1.3407   0.01730   0.01099  -0.0645   0.0092   1.0000
   9.750   1.3585   0.01796   0.01172  -0.0631   0.0089   1.0000
  10.000   1.3747   0.01869   0.01252  -0.0616   0.0086   1.0000
  10.250   1.3889   0.01944   0.01334  -0.0597   0.0083   1.0000
  10.500   1.3995   0.02021   0.01417  -0.0573   0.0081   1.0000
  10.750   1.4081   0.02108   0.01510  -0.0547   0.0078   1.0000
  11.000   1.4152   0.02210   0.01620  -0.0521   0.0075   1.0000
  11.250   1.4191   0.02340   0.01760  -0.0495   0.0073   1.0000
  11.500   1.4179   0.02516   0.01947  -0.0466   0.0071   1.0000
  11.750   1.4128   0.02739   0.02183  -0.0438   0.0069   1.0000
  12.000   1.4132   0.02936   0.02391  -0.0417   0.0068   1.0000
  12.250   1.4202   0.03087   0.02551  -0.0405   0.0067   1.0000
  12.500   1.4250   0.03264   0.02737  -0.0392   0.0067   1.0000
  12.750   1.4288   0.03461   0.02944  -0.0381   0.0066   1.0000
  13.000   1.4303   0.03687   0.03180  -0.0370   0.0065   1.0000
  13.250   1.4336   0.03904   0.03407  -0.0362   0.0064   1.0000
  13.500   1.4353   0.04146   0.03659  -0.0356   0.0064   1.0000
  13.750   1.4347   0.04422   0.03947  -0.0350   0.0063   1.0000
  14.000   1.4359   0.04687   0.04223  -0.0347   0.0062   1.0000
  14.250   1.4335   0.05002   0.04550  -0.0345   0.0062   1.0000
  14.500   1.4318   0.05322   0.04881  -0.0346   0.0061   1.0000
  14.750   1.4307   0.05646   0.05217  -0.0349   0.0060   1.0000
  15.000   1.4271   0.06014   0.05597  -0.0354   0.0059   1.0000
  15.250   1.4235   0.06398   0.05992  -0.0362   0.0058   1.0000
  15.500   1.4199   0.06799   0.06405  -0.0372   0.0058   1.0000
  15.750   1.4170   0.07202   0.06818  -0.0386   0.0056   1.0000
  16.000   1.4131   0.07635   0.07261  -0.0402   0.0055   1.0000
  16.250   1.4062   0.08132   0.07771  -0.0420   0.0054   1.0000
  16.500   1.3985   0.08659   0.08310  -0.0442   0.0054   1.0000
  16.750   1.3907   0.09204   0.08866  -0.0466   0.0053   1.0000
  17.000   1.3829   0.09767   0.09440  -0.0492   0.0052   1.0000
  17.250   1.3716   0.10408   0.10096  -0.0523   0.0052   1.0000
  17.500   1.3631   0.11013   0.10712  -0.0554   0.0052   1.0000
  17.750   1.3525   0.11674   0.11384  -0.0589   0.0051   1.0000
  18.000   1.3421   0.12348   0.12071  -0.0626   0.0051   1.0000
  18.250   1.3307   0.13059   0.12793  -0.0666   0.0051   1.0000
  18.500   1.3185   0.13802   0.13550  -0.0710   0.0051   1.0000
  18.750   1.3074   0.14539   0.14299  -0.0754   0.0050   1.0000
  19.000   1.2957   0.15305   0.15076  -0.0802   0.0050   1.0000
  19.250   1.2843   0.16087   0.15870  -0.0851   0.0050   1.0000
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