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E197 (13.49%) (e197-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: E197 (13.49%) (e197-il)
Reynolds number: 50,000
Max Cl/Cd: 29 at α=10.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e197-il-50000.txt
Download as CSV file: xf-e197-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E197  (13.49%)                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3293   0.10123   0.09459  -0.0270   1.0000   0.3072
  -8.750  -0.3511   0.10017   0.09370  -0.0272   1.0000   0.3167
  -8.500  -0.3389   0.09578   0.08935  -0.0271   1.0000   0.3184
  -8.250  -0.4635   0.07744   0.07152  -0.0484   1.0000   0.1506
  -8.000  -0.5188   0.07180   0.06597  -0.0489   1.0000   0.1371
  -7.750  -0.5304   0.06942   0.06367  -0.0458   1.0000   0.1348
  -7.500  -0.5540   0.06693   0.06121  -0.0427   1.0000   0.1322
  -7.250  -0.6010   0.06195   0.05580  -0.0411   1.0000   0.1231
  -7.000  -0.6068   0.05902   0.05277  -0.0390   1.0000   0.1220
  -6.750  -0.6118   0.05581   0.04935  -0.0373   1.0000   0.1210
  -6.500  -0.6136   0.05248   0.04571  -0.0359   1.0000   0.1205
  -6.250  -0.6113   0.04916   0.04198  -0.0346   1.0000   0.1206
  -6.000  -0.6043   0.04603   0.03837  -0.0335   1.0000   0.1207
  -5.750  -0.5930   0.04306   0.03490  -0.0325   1.0000   0.1211
  -5.500  -0.5785   0.04040   0.03171  -0.0314   1.0000   0.1221
  -5.250  -0.5618   0.03813   0.02884  -0.0304   1.0000   0.1241
  -5.000  -0.5449   0.03632   0.02711  -0.0295   1.0000   0.1308
  -4.750  -0.5266   0.03470   0.02504  -0.0285   1.0000   0.1392
  -4.500  -0.5079   0.03321   0.02352  -0.0274   1.0000   0.1497
  -4.250  -0.4886   0.03176   0.02190  -0.0263   1.0000   0.1678
  -4.000  -0.4615   0.03033   0.02079  -0.0268   0.9964   0.2054
  -3.750  -0.4304   0.02896   0.01998  -0.0281   0.9899   0.2913
  -3.500  -0.4014   0.02846   0.02030  -0.0282   0.9833   0.4153
  -3.250  -0.3816   0.02855   0.02082  -0.0260   0.9764   0.5177
  -3.000  -0.3582   0.02902   0.02146  -0.0240   0.9698   0.6024
  -2.750  -0.3420   0.02923   0.02176  -0.0209   0.9630   0.6637
  -2.500  -0.3193   0.02966   0.02223  -0.0185   0.9568   0.7229
  -2.250  -0.3068   0.02970   0.02228  -0.0150   0.9504   0.7714
  -2.000  -0.2859   0.02998   0.02254  -0.0124   0.9442   0.8239
  -1.750  -0.2561   0.03038   0.02288  -0.0118   0.9381   0.8815
  -1.500  -0.1405   0.03206   0.02409  -0.0272   0.9300   0.9484
  -1.250   0.0206   0.03331   0.02469  -0.0538   0.9228   0.9993
  -1.000   0.0066   0.03281   0.02412  -0.0511   0.9154   1.0000
  -0.750  -0.0131   0.03236   0.02353  -0.0470   0.9089   1.0000
  -0.500  -0.0085   0.03255   0.02346  -0.0456   0.9025   1.0000
  -0.250   0.0195   0.03327   0.02388  -0.0475   0.8963   1.0000
   0.000   0.0295   0.03381   0.02422  -0.0463   0.8903   1.0000
   0.250   0.0569   0.03466   0.02484  -0.0477   0.8842   1.0000
   0.500   0.0747   0.03546   0.02547  -0.0475   0.8787   1.0000
   0.750   0.0920   0.03627   0.02611  -0.0473   0.8729   1.0000
   1.000   0.1267   0.03740   0.02707  -0.0496   0.8669   1.0000
   1.250   0.1330   0.03817   0.02773  -0.0477   0.8621   1.0000
   1.500   0.1523   0.03915   0.02859  -0.0478   0.8567   1.0000
   1.750   0.1814   0.04034   0.02967  -0.0493   0.8509   1.0000
   2.000   0.1895   0.04128   0.03053  -0.0478   0.8465   1.0000
   2.250   0.2075   0.04239   0.03157  -0.0478   0.8418   1.0000
   2.500   0.2361   0.04372   0.03283  -0.0492   0.8357   1.0000
   2.750   0.2433   0.04480   0.03386  -0.0478   0.8322   1.0000
   3.000   0.2568   0.04602   0.03504  -0.0473   0.8287   1.0000
   3.250   0.2894   0.04753   0.03652  -0.0492   0.8209   1.0000
   3.500   0.2960   0.04881   0.03777  -0.0480   0.8190   1.0000
   3.750   0.3051   0.05014   0.03910  -0.0472   0.8166   1.0000
   4.000   0.3159   0.05163   0.04058  -0.0467   0.8157   1.0000
   4.250   0.3264   0.05322   0.04217  -0.0464   0.8163   1.0000
   4.500   0.3398   0.05510   0.04406  -0.0466   0.8196   1.0000
   6.250   0.4944   0.06669   0.05603  -0.0503   0.7312   1.0000
   6.500   0.4976   0.06902   0.05843  -0.0500   0.7316   1.0000
   6.750   0.5073   0.07161   0.06109  -0.0503   0.7307   1.0000
   7.000   0.5596   0.07039   0.06001  -0.0491   0.6661   1.0000
   7.250   0.5833   0.07165   0.06139  -0.0489   0.6458   1.0000
   7.500   0.6202   0.07256   0.06247  -0.0491   0.6239   1.0000
   7.750   0.6317   0.07409   0.06410  -0.0482   0.6058   1.0000
   8.000   0.6523   0.07537   0.06552  -0.0476   0.5869   1.0000
   8.250   0.7027   0.07521   0.06559  -0.0477   0.5659   1.0000
   8.500   0.7028   0.07720   0.06769  -0.0463   0.5472   1.0000
   8.750   0.7215   0.07828   0.06893  -0.0453   0.5276   1.0000
   9.000   0.7775   0.07663   0.06758  -0.0443   0.5072   1.0000
   9.250   0.7705   0.07931   0.07032  -0.0430   0.4874   1.0000
   9.500   0.8053   0.07851   0.06980  -0.0413   0.4663   1.0000
   9.750   0.8308   0.07818   0.06969  -0.0394   0.4451   1.0000
  10.000   0.8930   0.07277   0.06473  -0.0358   0.4214   1.0000
  10.250   0.9098   0.07238   0.06453  -0.0333   0.3978   1.0000
  10.500   1.1532   0.03977   0.03185  -0.0206   0.2888   1.0000
  10.750   1.1491   0.04182   0.03363  -0.0171   0.2538   1.0000
  11.000   1.1570   0.04389   0.03518  -0.0146   0.2165   1.0000
  11.250   1.1615   0.04639   0.03747  -0.0124   0.1877   1.0000
  11.500   1.1617   0.04907   0.04012  -0.0102   0.1658   1.0000
  11.750   1.1715   0.05182   0.04270  -0.0086   0.1439   1.0000
  12.000   1.1759   0.05479   0.04571  -0.0070   0.1279   1.0000
  12.250   1.1838   0.05792   0.04889  -0.0057   0.1151   1.0000
  12.500   1.1971   0.06128   0.05228  -0.0048   0.1047   1.0000
  12.750   1.1884   0.06499   0.05637  -0.0032   0.1007   1.0000
  13.000   1.2075   0.06880   0.06013  -0.0028   0.0931   1.0000
  13.250   1.1899   0.07284   0.06454  -0.0015   0.0922   1.0000
  13.500   1.1695   0.07734   0.06937  -0.0009   0.0916   1.0000
  13.750   1.1487   0.08234   0.07466  -0.0011   0.0914   1.0000
  14.000   1.1244   0.08796   0.08054  -0.0020   0.0915   1.0000
  14.250   1.0996   0.09416   0.08696  -0.0036   0.0920   1.0000
  14.500   1.0759   0.10084   0.09382  -0.0059   0.0928   1.0000
  14.750   1.0536   0.10798   0.10109  -0.0087   0.0935   1.0000
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