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I.S.A. 571 (isa571-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: I.S.A. 571 (isa571-il)
Reynolds number: 50,000
Max Cl/Cd: 35.38 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-isa571-il-50000.txt
Download as CSV file: xf-isa571-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4294   0.10691   0.10019  -0.0163   1.0000   0.1508
  -8.250  -0.4124   0.10132   0.09460  -0.0145   1.0000   0.1569
  -8.000  -0.4171   0.09926   0.09265  -0.0147   1.0000   0.1631
  -7.750  -0.4317   0.09884   0.09239  -0.0213   1.0000   0.1660
  -7.500  -0.4134   0.09311   0.08665  -0.0153   1.0000   0.1769
  -7.250  -0.4131   0.08997   0.08361  -0.0163   1.0000   0.1837
  -7.000  -0.4149   0.08808   0.08177  -0.0201   1.0000   0.1944
  -6.750  -0.4068   0.08416   0.07791  -0.0174   1.0000   0.2072
  -6.500  -0.4010   0.08076   0.07458  -0.0165   1.0000   0.2199
  -6.250  -0.3960   0.07758   0.07146  -0.0164   1.0000   0.2340
  -6.000  -0.3927   0.07518   0.06906  -0.0203   1.0000   0.2528
  -5.750  -0.3850   0.07128   0.06523  -0.0168   1.0000   0.2694
  -5.500  -0.3789   0.06861   0.06258  -0.0168   1.0000   0.2970
  -5.250  -0.0271   0.04348   0.03642  -0.0205   1.0000   1.0000
  -5.000  -0.0168   0.04139   0.03435  -0.0213   1.0000   1.0000
  -4.750  -0.0067   0.03938   0.03239  -0.0220   1.0000   1.0000
  -4.500  -0.0417   0.04023   0.03342  -0.0118   1.0000   0.9771
  -4.250  -0.0983   0.04201   0.03550   0.0022   1.0000   0.9324
  -4.000  -0.1526   0.04311   0.03689   0.0140   1.0000   0.8861
  -3.750  -0.2004   0.04343   0.03748   0.0233   1.0000   0.8449
  -3.250  -0.1239   0.03463   0.02587  -0.0471   1.0000   0.1930
  -3.000  -0.0930   0.03195   0.02280  -0.0478   1.0000   0.1868
  -2.750  -0.0591   0.03000   0.02011  -0.0486   1.0000   0.1809
  -2.500  -0.0294   0.02814   0.01789  -0.0487   1.0000   0.1814
  -2.250  -0.0020   0.02665   0.01620  -0.0487   1.0000   0.1900
  -2.000   0.0268   0.02546   0.01466  -0.0486   1.0000   0.1921
  -1.750   0.0545   0.02442   0.01341  -0.0483   1.0000   0.1974
  -1.500   0.0812   0.02363   0.01251  -0.0480   1.0000   0.2113
  -1.250   0.1092   0.02296   0.01171  -0.0477   1.0000   0.2227
  -1.000   0.1365   0.02232   0.01104  -0.0475   1.0000   0.2383
  -0.750   0.1643   0.02158   0.01053  -0.0478   1.0000   0.2706
  -0.500   0.1804   0.01874   0.01025  -0.0455   1.0000   1.0000
  -0.250   0.2044   0.01928   0.00997  -0.0446   1.0000   1.0000
   0.000   0.2249   0.01990   0.01030  -0.0444   1.0000   1.0000
   0.250   0.2438   0.02067   0.01088  -0.0444   1.0000   1.0000
   0.500   0.2609   0.02163   0.01173  -0.0446   1.0000   1.0000
   0.750   0.3197   0.02271   0.01265  -0.0525   0.9796   1.0000
   1.000   0.3940   0.02328   0.01311  -0.0623   0.9465   1.0000
   1.250   0.4606   0.02332   0.01312  -0.0697   0.9110   1.0000
   1.500   0.5255   0.02291   0.01275  -0.0758   0.8766   1.0000
   1.750   0.5848   0.02220   0.01206  -0.0800   0.8450   1.0000
   2.000   0.6295   0.02176   0.01165  -0.0815   0.8100   1.0000
   2.250   0.6714   0.02144   0.01127  -0.0824   0.7777   1.0000
   2.500   0.7077   0.02135   0.01108  -0.0823   0.7462   1.0000
   2.750   0.7385   0.02152   0.01112  -0.0814   0.7145   1.0000
   3.000   0.7659   0.02192   0.01146  -0.0803   0.6841   1.0000
   3.250   0.7933   0.02242   0.01184  -0.0793   0.6574   1.0000
   3.500   0.8181   0.02314   0.01256  -0.0784   0.6328   1.0000
   3.750   0.8439   0.02388   0.01328  -0.0776   0.6110   1.0000
   4.000   0.8685   0.02469   0.01417  -0.0768   0.5896   1.0000
   4.250   0.8942   0.02546   0.01492  -0.0759   0.5697   1.0000
   4.500   0.9170   0.02639   0.01596  -0.0749   0.5481   1.0000
   4.750   0.9420   0.02724   0.01683  -0.0740   0.5285   1.0000
   5.000   0.9646   0.02830   0.01806  -0.0730   0.5079   1.0000
   5.250   0.9882   0.02920   0.01900  -0.0718   0.4865   1.0000
   5.500   1.0102   0.03025   0.02013  -0.0705   0.4648   1.0000
   5.750   1.0331   0.03117   0.02109  -0.0692   0.4431   1.0000
   6.000   1.0541   0.03226   0.02232  -0.0678   0.4217   1.0000
   6.250   1.0754   0.03355   0.02377  -0.0666   0.4028   1.0000
   6.500   1.0975   0.03484   0.02518  -0.0654   0.3854   1.0000
   6.750   1.1198   0.03618   0.02666  -0.0643   0.3689   1.0000
   7.000   1.1407   0.03782   0.02852  -0.0632   0.3538   1.0000
   7.250   1.1598   0.03969   0.03072  -0.0619   0.3394   1.0000
   7.500   1.1747   0.04135   0.03273  -0.0601   0.3216   1.0000
   7.750   1.1949   0.04004   0.03137  -0.0577   0.2903   1.0000
   8.000   1.2131   0.03806   0.02929  -0.0550   0.2568   1.0000
   8.250   1.2231   0.03684   0.02806  -0.0515   0.2206   1.0000
   8.500   1.2236   0.03725   0.02795  -0.0470   0.1703   1.0000
   8.750   1.2230   0.03999   0.03051  -0.0432   0.1310   1.0000
   9.000   1.2315   0.04272   0.03335  -0.0405   0.1119   1.0000
   9.250   1.2451   0.04560   0.03625  -0.0386   0.1012   1.0000
   9.500   1.2585   0.04843   0.03917  -0.0368   0.0930   1.0000
   9.750   1.2658   0.05205   0.04317  -0.0347   0.0878   1.0000
  10.000   1.2707   0.05543   0.04687  -0.0326   0.0833   1.0000
  10.250   1.2792   0.05910   0.05068  -0.0311   0.0802   1.0000
  10.500   1.2822   0.06390   0.05569  -0.0295   0.0787   1.0000
  10.750   1.2705   0.06819   0.06040  -0.0269   0.0785   1.0000
  11.000   1.2538   0.07235   0.06488  -0.0243   0.0785   1.0000
  11.250   1.2347   0.07683   0.06962  -0.0225   0.0786   1.0000
  11.500   1.2137   0.08172   0.07479  -0.0218   0.0789   1.0000
  11.750   1.1179   0.09535   0.08900  -0.0319   0.0867   1.0000
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