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S7012 8.75% (s7012-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S7012 8.75% (s7012-il)
Reynolds number: 100,000
Max Cl/Cd: 51.93 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s7012-il-100000.txt
Download as CSV file: xf-s7012-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S7012 8.75%                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4577   0.08904   0.08433  -0.0184   1.0000   0.1025
  -7.750  -0.4631   0.08584   0.08123  -0.0209   1.0000   0.1066
  -7.500  -0.4918   0.08122   0.07665  -0.0350   1.0000   0.1093
  -7.250  -0.4665   0.07825   0.07379  -0.0249   1.0000   0.1135
  -7.000  -0.4672   0.07430   0.06986  -0.0297   1.0000   0.1210
  -6.750  -0.4693   0.06934   0.06490  -0.0342   1.0000   0.1252
  -6.250  -0.4525   0.06325   0.05887  -0.0330   1.0000   0.1430
  -6.000  -0.4483   0.05927   0.05482  -0.0356   1.0000   0.1542
  -5.750  -0.4405   0.05581   0.05128  -0.0370   1.0000   0.1673
  -5.500  -0.4300   0.05272   0.04810  -0.0373   1.0000   0.1810
  -5.250  -0.4182   0.04969   0.04505  -0.0368   1.0000   0.1953
  -5.000  -0.3761   0.03358   0.02683  -0.0447   1.0000   0.0664
  -4.750  -0.3522   0.02934   0.02170  -0.0439   1.0000   0.0569
  -4.500  -0.3292   0.02700   0.01901  -0.0428   1.0000   0.0548
  -4.250  -0.3062   0.02446   0.01616  -0.0420   1.0000   0.0538
  -4.000  -0.2825   0.02244   0.01383  -0.0409   1.0000   0.0537
  -3.750  -0.2587   0.02082   0.01197  -0.0398   1.0000   0.0546
  -3.500  -0.2358   0.01913   0.01023  -0.0388   1.0000   0.0582
  -3.250  -0.2134   0.01812   0.00924  -0.0379   1.0000   0.0662
  -3.000  -0.1908   0.01682   0.00801  -0.0370   1.0000   0.0764
  -2.750  -0.1655   0.01457   0.00652  -0.0368   1.0000   0.1828
  -2.500  -0.1522   0.01248   0.00671  -0.0342   1.0000   0.6473
  -2.250  -0.1438   0.01246   0.00696  -0.0294   1.0000   0.7667
  -2.000  -0.1385   0.01248   0.00709  -0.0241   1.0000   0.8419
  -1.750  -0.1284   0.01243   0.00708  -0.0198   1.0000   0.9220
  -1.500  -0.0849   0.01241   0.00679  -0.0241   0.9983   1.0000
  -1.250  -0.0279   0.01272   0.00676  -0.0308   0.9858   1.0000
  -1.000   0.0271   0.01294   0.00671  -0.0369   0.9727   1.0000
  -0.750   0.0805   0.01308   0.00661  -0.0425   0.9592   1.0000
  -0.500   0.1330   0.01312   0.00648  -0.0477   0.9455   1.0000
  -0.250   0.1856   0.01308   0.00629  -0.0526   0.9320   1.0000
   0.000   0.2351   0.01298   0.00610  -0.0568   0.9177   1.0000
   0.250   0.2806   0.01287   0.00590  -0.0599   0.9022   1.0000
   0.500   0.3219   0.01275   0.00570  -0.0621   0.8860   1.0000
   0.750   0.3536   0.01274   0.00562  -0.0625   0.8653   1.0000
   1.000   0.3854   0.01273   0.00553  -0.0627   0.8462   1.0000
   1.250   0.4139   0.01278   0.00551  -0.0623   0.8261   1.0000
   1.500   0.4408   0.01288   0.00553  -0.0616   0.8057   1.0000
   1.750   0.4680   0.01299   0.00554  -0.0609   0.7871   1.0000
   2.000   0.4932   0.01318   0.00568  -0.0601   0.7660   1.0000
   2.250   0.5194   0.01335   0.00578  -0.0593   0.7470   1.0000
   2.500   0.5453   0.01356   0.00595  -0.0586   0.7281   1.0000
   2.750   0.5709   0.01380   0.00615  -0.0578   0.7085   1.0000
   3.000   0.5969   0.01403   0.00632  -0.0571   0.6901   1.0000
   3.250   0.6227   0.01428   0.00654  -0.0564   0.6711   1.0000
   3.500   0.6482   0.01454   0.00684  -0.0557   0.6515   1.0000
   3.750   0.6741   0.01480   0.00706  -0.0549   0.6329   1.0000
   4.000   0.6996   0.01509   0.00736  -0.0542   0.6128   1.0000
   4.250   0.7251   0.01536   0.00763  -0.0535   0.5926   1.0000
   4.500   0.7505   0.01565   0.00795  -0.0527   0.5719   1.0000
   4.750   0.7756   0.01593   0.00825  -0.0519   0.5499   1.0000
   5.000   0.8005   0.01622   0.00858  -0.0510   0.5269   1.0000
   5.250   0.8255   0.01651   0.00885  -0.0502   0.5040   1.0000
   5.500   0.8497   0.01680   0.00922  -0.0492   0.4778   1.0000
   5.750   0.8734   0.01709   0.00954  -0.0482   0.4496   1.0000
   6.000   0.8966   0.01739   0.00986  -0.0471   0.4191   1.0000
   6.250   0.9190   0.01771   0.01026  -0.0460   0.3840   1.0000
   6.500   0.9405   0.01811   0.01064  -0.0447   0.3451   1.0000
   6.750   0.9606   0.01867   0.01117  -0.0434   0.2993   1.0000
   7.000   0.9790   0.01949   0.01185  -0.0421   0.2473   1.0000
   7.250   0.9947   0.02075   0.01282  -0.0406   0.1860   1.0000
   7.500   1.0064   0.02272   0.01430  -0.0390   0.1137   1.0000
   7.750   1.0158   0.02545   0.01670  -0.0366   0.0712   1.0000
   8.000   1.0292   0.02770   0.01881  -0.0348   0.0558   1.0000
   8.250   1.0470   0.02986   0.02107  -0.0332   0.0482   1.0000
   8.500   1.0665   0.03238   0.02353  -0.0321   0.0440   1.0000
   8.750   1.0894   0.03573   0.02710  -0.0313   0.0419   1.0000
   9.000   1.1100   0.03871   0.03046  -0.0301   0.0408   1.0000
   9.250   1.1266   0.04216   0.03435  -0.0287   0.0403   1.0000
   9.500   1.1380   0.04582   0.03849  -0.0270   0.0400   1.0000
   9.750   1.1440   0.04949   0.04264  -0.0252   0.0395   1.0000
  10.000   1.1450   0.05319   0.04678  -0.0233   0.0388   1.0000
  10.250   1.1406   0.05706   0.05105  -0.0213   0.0385   1.0000
  10.500   1.1305   0.06100   0.05535  -0.0194   0.0386   1.0000
  10.750   1.1137   0.06478   0.05940  -0.0174   0.0389   1.0000
  11.000   1.0945   0.06887   0.06371  -0.0165   0.0392   1.0000
  11.250   1.0739   0.07368   0.06872  -0.0173   0.0398   1.0000
  11.500   1.0528   0.07922   0.07444  -0.0196   0.0403   1.0000
  11.750   1.0323   0.08557   0.08092  -0.0230   0.0410   1.0000
  12.000   1.0116   0.09277   0.08823  -0.0275   0.0415   1.0000
  12.250   0.9957   0.10024   0.09575  -0.0316   0.0423   1.0000
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