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I.S.A. 571 (isa571-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: I.S.A. 571 (isa571-il)
Reynolds number: 1,000,000
Max Cl/Cd: 100.5 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-isa571-il-1000000-n5.txt
Download as CSV file: xf-isa571-il-1000000-n5.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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4196   0.09044   0.08889  -0.0193   1.0000   0.0037
  -8.750  -0.4282   0.08764   0.08611  -0.0182   1.0000   0.0037
  -8.250  -0.4382   0.01883   0.01542  -0.0835   0.9868   0.0039
  -8.000  -0.4132   0.01599   0.01218  -0.0842   0.9847   0.0041
  -7.750  -0.3849   0.01455   0.01051  -0.0849   0.9828   0.0043
  -7.500  -0.3537   0.01354   0.00935  -0.0859   0.9811   0.0044
  -7.250  -0.3204   0.01272   0.00838  -0.0873   0.9796   0.0047
  -7.000  -0.2867   0.01199   0.00752  -0.0888   0.9780   0.0049
  -6.750  -0.2573   0.01136   0.00678  -0.0891   0.9741   0.0052
  -6.500  -0.2277   0.01081   0.00613  -0.0895   0.9696   0.0056
  -6.250  -0.1960   0.01035   0.00558  -0.0903   0.9661   0.0059
  -6.000  -0.1698   0.00976   0.00488  -0.0899   0.9596   0.0064
  -5.750  -0.1401   0.00927   0.00432  -0.0903   0.9549   0.0071
  -5.500  -0.1119   0.00891   0.00390  -0.0903   0.9491   0.0076
  -5.250  -0.0828   0.00857   0.00350  -0.0904   0.9409   0.0084
  -5.000  -0.0543   0.00830   0.00315  -0.0904   0.9288   0.0090
  -4.750  -0.0260   0.00796   0.00273  -0.0903   0.9136   0.0110
  -4.500   0.0018   0.00772   0.00241  -0.0902   0.8970   0.0132
  -4.250   0.0292   0.00754   0.00217  -0.0899   0.8762   0.0184
  -4.000   0.0558   0.00751   0.00209  -0.0895   0.8459   0.0266
  -3.750   0.0815   0.00763   0.00201  -0.0888   0.8014   0.0297
  -3.500   0.1061   0.00780   0.00192  -0.0880   0.7407   0.0320
  -3.250   0.1311   0.00802   0.00191  -0.0873   0.6811   0.0339
  -3.000   0.1573   0.00818   0.00190  -0.0869   0.6389   0.0358
  -2.750   0.1842   0.00828   0.00186  -0.0867   0.6088   0.0374
  -2.500   0.2113   0.00838   0.00183  -0.0865   0.5803   0.0383
  -2.250   0.2384   0.00842   0.00175  -0.0863   0.5505   0.0388
  -2.000   0.2654   0.00834   0.00151  -0.0861   0.5189   0.0405
  -1.750   0.2922   0.00839   0.00142  -0.0859   0.4813   0.0420
  -1.500   0.3190   0.00851   0.00137  -0.0857   0.4441   0.0434
  -1.250   0.3459   0.00861   0.00133  -0.0856   0.4133   0.0446
  -0.750   0.4003   0.00879   0.00129  -0.0853   0.3652   0.0470
  -0.500   0.4279   0.00884   0.00128  -0.0853   0.3527   0.0481
  -0.250   0.4555   0.00889   0.00127  -0.0852   0.3415   0.0489
   0.000   0.4832   0.00893   0.00127  -0.0852   0.3315   0.0509
   0.250   0.5108   0.00897   0.00128  -0.0851   0.3222   0.0554
   0.500   0.5384   0.00902   0.00131  -0.0851   0.3123   0.0607
   0.750   0.5661   0.00902   0.00138  -0.0851   0.3047   0.0946
   1.000   0.5936   0.00910   0.00143  -0.0851   0.2967   0.1003
   1.250   0.6212   0.00914   0.00148  -0.0851   0.2891   0.1061
   1.500   0.6486   0.00922   0.00154  -0.0850   0.2810   0.1096
   1.750   0.6762   0.00929   0.00160  -0.0850   0.2733   0.1125
   2.000   0.7035   0.00937   0.00167  -0.0850   0.2638   0.1182
   2.250   0.7307   0.00947   0.00176  -0.0849   0.2529   0.1256
   2.750   0.7784   0.00799   0.00214  -0.0839   0.2225   1.0000
   3.000   0.8045   0.00829   0.00230  -0.0837   0.1954   1.0000
   3.250   0.8308   0.00855   0.00248  -0.0835   0.1785   1.0000
   3.500   0.8574   0.00877   0.00264  -0.0834   0.1682   1.0000
   3.750   0.8843   0.00894   0.00280  -0.0833   0.1622   1.0000
   4.000   0.9108   0.00916   0.00298  -0.0831   0.1550   1.0000
   4.250   0.9376   0.00934   0.00316  -0.0830   0.1478   1.0000
   4.500   0.9638   0.00959   0.00336  -0.0829   0.1368   1.0000
   4.750   0.9892   0.00995   0.00360  -0.0826   0.1142   1.0000
   5.000   1.0132   0.01048   0.00396  -0.0821   0.0842   1.0000
   5.250   1.0389   0.01079   0.00424  -0.0819   0.0760   1.0000
   5.500   1.0650   0.01102   0.00448  -0.0817   0.0709   1.0000
   5.750   1.0879   0.01168   0.00495  -0.0810   0.0387   1.0000
   6.000   1.1108   0.01235   0.00552  -0.0803   0.0137   1.0000
   6.250   1.1354   0.01276   0.00595  -0.0799   0.0100   1.0000
   6.500   1.1604   0.01310   0.00632  -0.0796   0.0085   1.0000
   6.750   1.1850   0.01348   0.00673  -0.0791   0.0074   1.0000
   7.000   1.2087   0.01396   0.00724  -0.0786   0.0062   1.0000
   7.250   1.2330   0.01434   0.00766  -0.0781   0.0057   1.0000
   7.500   1.2570   0.01475   0.00810  -0.0777   0.0051   1.0000
   7.750   1.2803   0.01521   0.00862  -0.0771   0.0046   1.0000
   8.000   1.3023   0.01583   0.00930  -0.0763   0.0041   1.0000
   8.250   1.3250   0.01634   0.00986  -0.0756   0.0039   1.0000
   8.500   1.3472   0.01688   0.01047  -0.0749   0.0036   1.0000
   8.750   1.3688   0.01746   0.01111  -0.0741   0.0034   1.0000
   9.000   1.3899   0.01806   0.01177  -0.0732   0.0032   1.0000
   9.250   1.4107   0.01866   0.01243  -0.0723   0.0030   1.0000
   9.500   1.4306   0.01931   0.01314  -0.0713   0.0028   1.0000
   9.750   1.4468   0.02032   0.01426  -0.0697   0.0025   1.0000
  10.000   1.4655   0.02099   0.01501  -0.0685   0.0025   1.0000
  10.250   1.4825   0.02179   0.01590  -0.0671   0.0024   1.0000
  10.500   1.4980   0.02265   0.01687  -0.0654   0.0023   1.0000
  10.750   1.5119   0.02358   0.01790  -0.0636   0.0022   1.0000
  11.000   1.5241   0.02455   0.01897  -0.0615   0.0021   1.0000
  11.250   1.5325   0.02555   0.02007  -0.0588   0.0020   1.0000
  11.500   1.5389   0.02662   0.02124  -0.0558   0.0020   1.0000
  11.750   1.5447   0.02776   0.02249  -0.0530   0.0019   1.0000
  12.000   1.5491   0.02905   0.02390  -0.0502   0.0019   1.0000
  12.250   1.5525   0.03049   0.02544  -0.0477   0.0018   1.0000
  12.500   1.5549   0.03208   0.02714  -0.0453   0.0018   1.0000
  12.750   1.5564   0.03388   0.02905  -0.0432   0.0017   1.0000
  13.000   1.5553   0.03605   0.03135  -0.0414   0.0017   1.0000
  13.250   1.5537   0.03850   0.03391  -0.0401   0.0017   1.0000
  13.500   1.5491   0.04154   0.03708  -0.0393   0.0016   1.0000
  13.750   1.5428   0.04518   0.04087  -0.0394   0.0016   1.0000
  14.000   1.5341   0.04957   0.04540  -0.0403   0.0016   1.0000
  14.250   1.5235   0.05470   0.05068  -0.0421   0.0016   1.0000
  14.500   1.5101   0.06057   0.05671  -0.0444   0.0016   1.0000
  14.750   1.4943   0.06705   0.06334  -0.0472   0.0015   1.0000
  15.000   1.4767   0.07404   0.07048  -0.0502   0.0015   1.0000
  15.250   1.4577   0.08125   0.07782  -0.0532   0.0015   1.0000
  15.500   1.4372   0.08869   0.08540  -0.0562   0.0015   1.0000
  15.750   1.4173   0.09605   0.09288  -0.0592   0.0015   1.0000
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