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S7075 (9%) (s7075-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: S7075 (9%) (s7075-il)
Reynolds number: 500,000
Max Cl/Cd: 107.97 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s7075-il-500000.txt
Download as CSV file: xf-s7075-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S7075 (9%)                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4044   0.09021   0.08804  -0.0345   1.0000   0.0203
  -8.500  -0.4164   0.08809   0.08596  -0.0326   1.0000   0.0204
  -8.250  -0.4263   0.08539   0.08330  -0.0320   0.9997   0.0204
  -8.000  -0.4238   0.07745   0.07538  -0.0405   0.9957   0.0207
  -7.750  -0.4141   0.07373   0.07167  -0.0439   0.9927   0.0213
  -7.500  -0.3954   0.06817   0.06610  -0.0527   0.9882   0.0216
  -7.250  -0.3727   0.06315   0.06103  -0.0611   0.9851   0.0223
  -7.000  -0.3494   0.05721   0.05501  -0.0701   0.9819   0.0232
  -6.750  -0.3293   0.05055   0.04820  -0.0779   0.9763   0.0248
  -6.500  -0.2946   0.04325   0.04035  -0.0866   0.9728   0.0272
  -6.250  -0.2754   0.03374   0.03037  -0.0934   0.9705   0.0285
  -6.000  -0.2565   0.03170   0.02827  -0.0934   0.9655   0.0292
  -5.750  -0.2285   0.02938   0.02579  -0.0952   0.9627   0.0303
  -5.500  -0.1982   0.02041   0.01561  -0.0965   0.9600   0.0196
  -5.250  -0.1659   0.01736   0.01214  -0.0979   0.9585   0.0185
  -5.000  -0.1323   0.01558   0.01008  -0.0992   0.9571   0.0185
  -4.750  -0.1065   0.01450   0.00884  -0.0987   0.9531   0.0187
  -4.500  -0.0786   0.01361   0.00783  -0.0987   0.9493   0.0191
  -4.250  -0.0474   0.01302   0.00715  -0.0993   0.9466   0.0199
  -4.000  -0.0161   0.01226   0.00631  -0.0998   0.9442   0.0203
  -3.750   0.0143   0.01144   0.00542  -0.1003   0.9416   0.0206
  -3.500   0.0369   0.01070   0.00463  -0.0992   0.9355   0.0219
  -3.250   0.0655   0.01026   0.00416  -0.0991   0.9316   0.0241
  -3.000   0.0954   0.00990   0.00375  -0.0993   0.9285   0.0275
  -2.750   0.1204   0.00929   0.00328  -0.0986   0.9231   0.0624
  -2.500   0.1464   0.00878   0.00305  -0.0983   0.9181   0.1385
  -2.250   0.1744   0.00833   0.00286  -0.0984   0.9142   0.2183
  -2.000   0.1995   0.00794   0.00276  -0.0979   0.9082   0.3098
  -1.750   0.2255   0.00749   0.00264  -0.0976   0.9026   0.4153
  -1.500   0.2519   0.00700   0.00252  -0.0972   0.8981   0.5440
  -1.250   0.2746   0.00656   0.00252  -0.0960   0.8906   0.6775
  -1.000   0.2988   0.00629   0.00252  -0.0946   0.8849   0.7801
  -0.750   0.3230   0.00622   0.00251  -0.0934   0.8770   0.8238
  -0.500   0.3488   0.00613   0.00241  -0.0925   0.8703   0.8546
  -0.250   0.3726   0.00602   0.00235  -0.0913   0.8614   0.8776
   0.000   0.3975   0.00591   0.00223  -0.0901   0.8533   0.8990
   0.250   0.4215   0.00578   0.00213  -0.0889   0.8432   0.9223
   0.500   0.4508   0.00567   0.00204  -0.0887   0.8324   0.9516
   0.750   0.4910   0.00560   0.00192  -0.0912   0.8208   0.9830
   1.000   0.5229   0.00559   0.00185  -0.0920   0.8061   1.0000
   1.250   0.5491   0.00561   0.00180  -0.0915   0.7886   1.0000
   1.500   0.5755   0.00567   0.00176  -0.0911   0.7689   1.0000
   1.750   0.6016   0.00576   0.00175  -0.0906   0.7455   1.0000
   2.000   0.6274   0.00590   0.00176  -0.0901   0.7203   1.0000
   2.250   0.6529   0.00608   0.00180  -0.0895   0.6937   1.0000
   2.500   0.6780   0.00628   0.00188  -0.0888   0.6655   1.0000
   2.750   0.7029   0.00651   0.00197  -0.0882   0.6360   1.0000
   3.000   0.7277   0.00675   0.00208  -0.0875   0.6068   1.0000
   3.250   0.7524   0.00700   0.00220  -0.0869   0.5777   1.0000
   3.500   0.7769   0.00727   0.00235  -0.0862   0.5475   1.0000
   3.750   0.8012   0.00756   0.00251  -0.0855   0.5153   1.0000
   4.000   0.8250   0.00789   0.00269  -0.0848   0.4807   1.0000
   4.250   0.8489   0.00822   0.00288  -0.0841   0.4479   1.0000
   4.500   0.8729   0.00856   0.00310  -0.0834   0.4151   1.0000
   4.750   0.8962   0.00896   0.00333  -0.0827   0.3783   1.0000
   5.000   0.9195   0.00938   0.00358  -0.0819   0.3403   1.0000
   5.250   0.9424   0.00983   0.00386  -0.0812   0.3038   1.0000
   5.500   0.9658   0.01026   0.00416  -0.0805   0.2714   1.0000
   5.750   0.9887   0.01073   0.00448  -0.0798   0.2381   1.0000
   6.000   1.0113   0.01123   0.00482  -0.0790   0.2062   1.0000
   6.250   1.0340   0.01172   0.00519  -0.0782   0.1781   1.0000
   6.500   1.0566   0.01222   0.00558  -0.0775   0.1517   1.0000
   6.750   1.0787   0.01276   0.00599  -0.0767   0.1263   1.0000
   7.000   1.1003   0.01334   0.00645  -0.0758   0.1028   1.0000
   7.250   1.1213   0.01397   0.00696  -0.0748   0.0822   1.0000
   7.500   1.1425   0.01457   0.00751  -0.0738   0.0669   1.0000
   7.750   1.1629   0.01524   0.00812  -0.0726   0.0558   1.0000
   8.000   1.1834   0.01587   0.00874  -0.0715   0.0487   1.0000
   8.250   1.2031   0.01655   0.00946  -0.0702   0.0442   1.0000
   8.500   1.2239   0.01710   0.01007  -0.0691   0.0411   1.0000
   8.750   1.2423   0.01782   0.01081  -0.0677   0.0381   1.0000
   9.000   1.2561   0.01892   0.01198  -0.0656   0.0356   1.0000
   9.250   1.2752   0.01950   0.01265  -0.0642   0.0347   1.0000
   9.500   1.2928   0.02018   0.01341  -0.0627   0.0336   1.0000
   9.750   1.3087   0.02086   0.01416  -0.0609   0.0324   1.0000
  10.000   1.3247   0.02145   0.01481  -0.0592   0.0308   1.0000
  10.250   1.3381   0.02221   0.01561  -0.0571   0.0294   1.0000
  10.500   1.3456   0.02347   0.01694  -0.0542   0.0281   1.0000
  10.750   1.3531   0.02486   0.01844  -0.0515   0.0271   1.0000
  11.000   1.3688   0.02542   0.01908  -0.0500   0.0264   1.0000
  11.250   1.3816   0.02629   0.02006  -0.0482   0.0258   1.0000
  11.500   1.3946   0.02710   0.02097  -0.0465   0.0248   1.0000
  11.750   1.4065   0.02801   0.02197  -0.0447   0.0240   1.0000
  12.000   1.4186   0.02885   0.02288  -0.0431   0.0230   1.0000
  12.250   1.4281   0.02998   0.02409  -0.0414   0.0224   1.0000
  12.500   1.4351   0.03134   0.02551  -0.0395   0.0216   1.0000
  12.750   1.4353   0.03352   0.02780  -0.0372   0.0207   1.0000
  13.000   1.4385   0.03548   0.02991  -0.0353   0.0201   1.0000
  13.250   1.4485   0.03658   0.03112  -0.0341   0.0197   1.0000
  13.500   1.4570   0.03790   0.03257  -0.0330   0.0191   1.0000
  13.750   1.4658   0.03921   0.03399  -0.0320   0.0183   1.0000
  14.000   1.4734   0.04068   0.03555  -0.0312   0.0174   1.0000
  14.250   1.4822   0.04206   0.03701  -0.0306   0.0166   1.0000
  14.500   1.4860   0.04408   0.03908  -0.0300   0.0157   1.0000
  14.750   1.4783   0.04756   0.04267  -0.0295   0.0148   1.0000
  15.000   1.4940   0.04847   0.04372  -0.0295   0.0137   1.0000
  15.250   1.5064   0.04982   0.04513  -0.0296   0.0123   1.0000
  15.500   1.5072   0.05266   0.04799  -0.0299   0.0110   1.0000
  15.750   1.5054   0.05603   0.05151  -0.0304   0.0100   1.0000
  16.000   1.5035   0.05955   0.05517  -0.0311   0.0092   1.0000
  16.250   1.5001   0.06349   0.05922  -0.0323   0.0086   1.0000
  16.500   1.4911   0.06850   0.06434  -0.0342   0.0081   1.0000
  16.750   1.4759   0.07477   0.07075  -0.0368   0.0079   1.0000
  17.000   1.4584   0.08180   0.07794  -0.0401   0.0077   1.0000
  17.250   1.4403   0.08926   0.08557  -0.0438   0.0076   1.0000
  17.500   1.4229   0.09685   0.09333  -0.0478   0.0075   1.0000
  17.750   1.4046   0.10490   0.10154  -0.0521   0.0074   1.0000
  18.000   1.3841   0.11361   0.11041  -0.0569   0.0075   1.0000
  18.250   1.3639   0.12247   0.11942  -0.0620   0.0075   1.0000
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