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SD6080 (9.2%) (sd6080-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: SD6080 (9.2%) (sd6080-il)
Reynolds number: 100,000
Max Cl/Cd: 59.41 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd6080-il-100000.txt
Download as CSV file: xf-sd6080-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3398   0.10541   0.10058  -0.0300   1.0000   0.0777
  -8.750  -0.3480   0.10410   0.09938  -0.0341   1.0000   0.0791
  -8.500  -0.3592   0.10275   0.09816  -0.0381   1.0000   0.0795
  -8.250  -0.3359   0.09605   0.09144  -0.0346   1.0000   0.0816
  -8.000  -0.3242   0.09273   0.08814  -0.0333   1.0000   0.0845
  -7.750  -0.3218   0.09010   0.08558  -0.0336   1.0000   0.0874
  -7.500  -0.3268   0.08799   0.08358  -0.0340   1.0000   0.0900
  -7.250  -0.3435   0.08689   0.08265  -0.0331   1.0000   0.0915
  -7.000  -0.3654   0.08614   0.08204  -0.0325   1.0000   0.0924
  -6.750  -0.3899   0.08546   0.08146  -0.0334   1.0000   0.0931
  -6.500  -0.4079   0.08417   0.08015  -0.0366   1.0000   0.0936
  -6.250  -0.4097   0.08042   0.07653  -0.0319   1.0000   0.0946
  -6.000  -0.4104   0.07825   0.07444  -0.0264   1.0000   0.0963
  -5.750  -0.4129   0.07633   0.07257  -0.0240   1.0000   0.0984
  -5.500  -0.3719   0.06938   0.06535  -0.0424   0.9904   0.1089
  -5.250  -0.3481   0.06597   0.06203  -0.0413   0.9855   0.1130
  -5.000  -0.3131   0.06055   0.05638  -0.0515   0.9768   0.1247
  -4.750  -0.2787   0.05638   0.05207  -0.0576   0.9704   0.1394
  -4.500  -0.2497   0.05296   0.04857  -0.0612   0.9624   0.1547
  -4.250  -0.2161   0.04950   0.04502  -0.0650   0.9563   0.1714
  -4.000  -0.1830   0.04645   0.04171  -0.0700   0.9478   0.1975
  -3.750  -0.1276   0.03910   0.03338  -0.0791   0.9427   0.1527
  -3.500  -0.0804   0.02891   0.02143  -0.0807   0.9373   0.0630
  -3.250  -0.0388   0.02630   0.01826  -0.0830   0.9321   0.0618
  -3.000  -0.0018   0.02472   0.01620  -0.0843   0.9257   0.0650
  -2.750   0.0349   0.02304   0.01442  -0.0859   0.9192   0.0718
  -2.500   0.0808   0.02142   0.01273  -0.0888   0.9155   0.0852
  -2.250   0.1074   0.02043   0.01184  -0.0885   0.9062   0.1204
  -2.000   0.1462   0.01876   0.01098  -0.0907   0.9015   0.2646
  -1.750   0.1640   0.01722   0.01099  -0.0887   0.8927   0.6195
  -1.500   0.2266   0.01629   0.01042  -0.0935   0.8899   1.0000
  -1.250   0.2592   0.01642   0.01023  -0.0944   0.8820   1.0000
  -1.000   0.2913   0.01653   0.01007  -0.0950   0.8738   1.0000
  -0.750   0.3179   0.01676   0.01008  -0.0949   0.8646   1.0000
  -0.500   0.3517   0.01680   0.00991  -0.0956   0.8578   1.0000
  -0.250   0.3754   0.01708   0.01004  -0.0949   0.8477   1.0000
   0.000   0.4092   0.01707   0.00986  -0.0955   0.8418   1.0000
   0.250   0.4316   0.01739   0.01007  -0.0946   0.8311   1.0000
   0.500   0.4589   0.01756   0.01013  -0.0943   0.8229   1.0000
   0.750   0.4867   0.01768   0.01015  -0.0939   0.8146   1.0000
   1.000   0.5110   0.01796   0.01035  -0.0932   0.8049   1.0000
   1.250   0.5413   0.01792   0.01023  -0.0930   0.7982   1.0000
   1.500   0.5644   0.01824   0.01051  -0.0922   0.7875   1.0000
   1.750   0.5912   0.01836   0.01059  -0.0916   0.7789   1.0000
   2.000   0.6185   0.01842   0.01059  -0.0909   0.7701   1.0000
   2.250   0.6428   0.01866   0.01082  -0.0901   0.7595   1.0000
   2.500   0.6712   0.01861   0.01073  -0.0895   0.7516   1.0000
   2.750   0.6966   0.01874   0.01087  -0.0886   0.7411   1.0000
   3.000   0.7213   0.01893   0.01107  -0.0878   0.7300   1.0000
   3.250   0.7483   0.01893   0.01106  -0.0870   0.7205   1.0000
   3.500   0.7758   0.01885   0.01097  -0.0862   0.7106   1.0000
   3.750   0.8005   0.01899   0.01117  -0.0853   0.6984   1.0000
   4.000   0.8260   0.01906   0.01127  -0.0844   0.6863   1.0000
   4.250   0.8523   0.01904   0.01128  -0.0835   0.6745   1.0000
   4.500   0.8793   0.01896   0.01121  -0.0826   0.6626   1.0000
   4.750   0.9068   0.01883   0.01112  -0.0817   0.6505   1.0000
   5.000   0.9328   0.01879   0.01111  -0.0807   0.6366   1.0000
   5.250   0.9587   0.01876   0.01112  -0.0797   0.6218   1.0000
   5.500   0.9830   0.01882   0.01128  -0.0787   0.6050   1.0000
   5.750   1.0076   0.01884   0.01138  -0.0776   0.5871   1.0000
   6.000   1.0326   0.01879   0.01138  -0.0765   0.5685   1.0000
   6.250   1.0585   0.01870   0.01128  -0.0754   0.5494   1.0000
   6.500   1.0810   0.01879   0.01150  -0.0741   0.5256   1.0000
   6.750   1.1041   0.01886   0.01160  -0.0727   0.5006   1.0000
   7.000   1.1261   0.01902   0.01177  -0.0713   0.4726   1.0000
   7.250   1.1466   0.01930   0.01207  -0.0698   0.4409   1.0000
   7.500   1.1658   0.01974   0.01243  -0.0681   0.4069   1.0000
   7.750   1.1831   0.02037   0.01300  -0.0663   0.3701   1.0000
   8.000   1.1988   0.02119   0.01366  -0.0644   0.3338   1.0000
   8.250   1.2131   0.02218   0.01455  -0.0625   0.2976   1.0000
   8.500   1.2253   0.02328   0.01551  -0.0604   0.2632   1.0000
   8.750   1.2351   0.02443   0.01656  -0.0582   0.2290   1.0000
   9.000   1.2428   0.02562   0.01764  -0.0559   0.1962   1.0000
   9.250   1.2489   0.02694   0.01887  -0.0534   0.1667   1.0000
   9.500   1.2520   0.02846   0.02029  -0.0506   0.1392   1.0000
   9.750   1.2496   0.03034   0.02202  -0.0473   0.1123   1.0000
  10.000   1.2440   0.03279   0.02429  -0.0440   0.0875   1.0000
  10.250   1.2405   0.03551   0.02679  -0.0411   0.0725   1.0000
  10.500   1.2454   0.03775   0.02906  -0.0390   0.0629   1.0000
  10.750   1.2546   0.03998   0.03141  -0.0373   0.0560   1.0000
  11.000   1.2669   0.04226   0.03358  -0.0360   0.0510   1.0000
  11.250   1.2895   0.04484   0.03637  -0.0350   0.0480   1.0000
  11.500   1.3093   0.04755   0.03934  -0.0340   0.0457   1.0000
  11.750   1.3250   0.05053   0.04258  -0.0330   0.0442   1.0000
  12.000   1.3348   0.05365   0.04596  -0.0318   0.0430   1.0000
  12.250   1.3412   0.05685   0.04935  -0.0306   0.0419   1.0000
  12.500   1.3476   0.06118   0.05389  -0.0299   0.0407   1.0000
  12.750   1.3399   0.06582   0.05880  -0.0286   0.0402   1.0000
  13.000   1.3257   0.06942   0.06273  -0.0273   0.0400   1.0000
  13.250   1.3108   0.07362   0.06721  -0.0267   0.0400   1.0000
  13.500   1.2940   0.07825   0.07213  -0.0267   0.0400   1.0000
  13.750   1.2761   0.08338   0.07750  -0.0273   0.0400   1.0000
  14.000   1.2575   0.08903   0.08339  -0.0286   0.0401   1.0000
  14.250   1.2387   0.09475   0.08936  -0.0306   0.0403   1.0000
  14.500   1.2161   0.10069   0.09555  -0.0337   0.0406   1.0000
  14.750   0.9630   0.11484   0.11069  -0.0400   0.0486   1.0000
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