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I.S.A. 571 (isa571-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: I.S.A. 571 (isa571-il)
Reynolds number: 100,000
Max Cl/Cd: 51.58 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-isa571-il-100000.txt
Download as CSV file: xf-isa571-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: I.S.A. 571                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4030   0.09571   0.09087  -0.0186   1.0000   0.0675
  -8.000  -0.4096   0.09360   0.08886  -0.0197   1.0000   0.0691
  -7.750  -0.4128   0.09140   0.08673  -0.0265   1.0000   0.0703
  -7.500  -0.4097   0.08884   0.08410  -0.0346   1.0000   0.0708
  -7.250  -0.4029   0.08357   0.07899  -0.0229   1.0000   0.0739
  -7.000  -0.3972   0.08063   0.07608  -0.0232   1.0000   0.0777
  -6.750  -0.3869   0.07776   0.07313  -0.0321   1.0000   0.0825
  -6.500  -0.3794   0.07328   0.06864  -0.0338   1.0000   0.0841
  -6.250  -0.3736   0.06993   0.06539  -0.0301   1.0000   0.0864
  -6.000  -0.3629   0.06683   0.06227  -0.0304   1.0000   0.0906
  -5.750  -0.3397   0.06289   0.05802  -0.0383   1.0000   0.0970
  -5.500  -0.3324   0.05928   0.05456  -0.0354   1.0000   0.0995
  -5.250  -0.3153   0.05628   0.05145  -0.0364   1.0000   0.1065
  -5.000  -0.2959   0.05238   0.04739  -0.0387   1.0000   0.1124
  -4.750  -0.2728   0.04940   0.04415  -0.0410   1.0000   0.1244
  -4.500  -0.2531   0.04661   0.04122  -0.0417   1.0000   0.1383
  -4.250  -0.2375   0.04358   0.03828  -0.0406   1.0000   0.1471
  -4.000  -0.2122   0.04092   0.03531  -0.0425   1.0000   0.1673
  -3.750  -0.1919   0.03804   0.03240  -0.0424   1.0000   0.1832
  -3.500  -0.1716   0.03571   0.03001  -0.0423   1.0000   0.2123
  -3.000  -0.0965   0.02935   0.02247  -0.0461   1.0000   0.1681
  -2.750  -0.0839   0.02818   0.02174  -0.0453   1.0000   0.2428
  -2.500  -0.0191   0.02366   0.01501  -0.0469   1.0000   0.1097
  -2.250   0.0091   0.02203   0.01338  -0.0474   1.0000   0.1160
  -2.000   0.0376   0.02106   0.01213  -0.0474   1.0000   0.1192
  -1.750   0.0648   0.02026   0.01117  -0.0475   1.0000   0.1259
  -1.500   0.0913   0.01959   0.01048  -0.0475   1.0000   0.1297
  -1.250   0.1170   0.01916   0.00999  -0.0474   1.0000   0.1345
  -1.000   0.1458   0.01870   0.00961  -0.0481   0.9988   0.1435
  -0.750   0.1987   0.01802   0.00907  -0.0532   0.9892   0.1604
  -0.500   0.2516   0.01722   0.00849  -0.0582   0.9785   0.2041
  -0.250   0.2957   0.01479   0.00802  -0.0606   0.9678   1.0000
   0.000   0.3455   0.01471   0.00773  -0.0648   0.9502   1.0000
   0.250   0.3954   0.01447   0.00736  -0.0688   0.9325   1.0000
   0.500   0.4458   0.01405   0.00688  -0.0725   0.9146   1.0000
   0.750   0.4875   0.01359   0.00637  -0.0743   0.8898   1.0000
   1.000   0.5290   0.01310   0.00584  -0.0759   0.8597   1.0000
   1.250   0.5690   0.01267   0.00529  -0.0769   0.8167   1.0000
   1.500   0.6055   0.01252   0.00488  -0.0773   0.7606   1.0000
   1.750   0.6357   0.01276   0.00478  -0.0768   0.7035   1.0000
   2.000   0.6619   0.01323   0.00489  -0.0758   0.6559   1.0000
   2.250   0.6869   0.01372   0.00512  -0.0749   0.6175   1.0000
   2.500   0.7122   0.01421   0.00540  -0.0742   0.5875   1.0000
   2.750   0.7377   0.01467   0.00576  -0.0737   0.5627   1.0000
   3.000   0.7634   0.01513   0.00607  -0.0731   0.5420   1.0000
   3.250   0.7889   0.01557   0.00644  -0.0726   0.5223   1.0000
   3.500   0.8145   0.01601   0.00683  -0.0721   0.5043   1.0000
   3.750   0.8399   0.01647   0.00725  -0.0716   0.4871   1.0000
   4.000   0.8653   0.01695   0.00765  -0.0711   0.4702   1.0000
   4.250   0.8902   0.01743   0.00811  -0.0706   0.4528   1.0000
   4.500   0.9148   0.01792   0.00861  -0.0699   0.4348   1.0000
   4.750   0.9394   0.01844   0.00915  -0.0693   0.4173   1.0000
   5.000   0.9640   0.01899   0.00969  -0.0687   0.4001   1.0000
   5.250   0.9885   0.01959   0.01026  -0.0682   0.3832   1.0000
   5.500   1.0123   0.02017   0.01091  -0.0675   0.3653   1.0000
   5.750   1.0362   0.02079   0.01162  -0.0668   0.3482   1.0000
   6.000   1.0601   0.02145   0.01239  -0.0661   0.3320   1.0000
   6.250   1.0836   0.02207   0.01311  -0.0653   0.3160   1.0000
   6.500   1.1056   0.02242   0.01348  -0.0643   0.2979   1.0000
   6.750   1.1252   0.02250   0.01369  -0.0629   0.2761   1.0000
   7.000   1.1454   0.02265   0.01399  -0.0616   0.2562   1.0000
   7.250   1.1650   0.02278   0.01428  -0.0603   0.2345   1.0000
   7.500   1.1838   0.02295   0.01454  -0.0590   0.2082   1.0000
   7.750   1.2010   0.02351   0.01509  -0.0575   0.1725   1.0000
   8.000   1.2122   0.02530   0.01647  -0.0553   0.0942   1.0000
   8.250   1.2175   0.02789   0.01879  -0.0523   0.0671   1.0000
   8.500   1.2291   0.02961   0.02065  -0.0498   0.0572   1.0000
   8.750   1.2383   0.03146   0.02257  -0.0472   0.0526   1.0000
   9.000   1.2491   0.03320   0.02444  -0.0447   0.0492   1.0000
   9.250   1.2583   0.03505   0.02631  -0.0424   0.0462   1.0000
   9.500   1.2677   0.03733   0.02865  -0.0401   0.0437   1.0000
   9.750   1.2803   0.03942   0.03095  -0.0381   0.0416   1.0000
  10.000   1.2943   0.04194   0.03366  -0.0364   0.0405   1.0000
  10.250   1.3078   0.04478   0.03674  -0.0347   0.0397   1.0000
  10.500   1.3184   0.04793   0.04018  -0.0329   0.0392   1.0000
  10.750   1.3235   0.05129   0.04390  -0.0306   0.0391   1.0000
  11.000   1.3204   0.05477   0.04775  -0.0276   0.0392   1.0000
  11.250   1.3106   0.05835   0.05169  -0.0246   0.0394   1.0000
  11.500   1.2963   0.06214   0.05582  -0.0221   0.0396   1.0000
  11.750   1.2787   0.06632   0.06031  -0.0205   0.0398   1.0000
  12.000   1.2583   0.07109   0.06538  -0.0202   0.0401   1.0000
  12.250   1.2358   0.07661   0.07117  -0.0213   0.0404   1.0000
  12.500   1.2118   0.08304   0.07785  -0.0241   0.0409   1.0000
  12.750   1.1865   0.09046   0.08549  -0.0283   0.0413   1.0000
  13.000   1.1598   0.09895   0.09414  -0.0338   0.0418   1.0000
  13.250   1.1315   0.10867   0.10400  -0.0405   0.0423   1.0000
  13.500   1.1023   0.11952   0.11496  -0.0479   0.0430   1.0000
  13.750   1.0754   0.13072   0.12621  -0.0549   0.0437   1.0000
  14.000   1.0572   0.14042   0.13591  -0.0601   0.0444   1.0000
  14.250   0.9967   0.16967   0.16497  -0.0774   0.0524   1.0000
  14.500   1.0000   0.17457   0.16990  -0.0788   0.0539   1.0000
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