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(Dicke 12.28%) (e171-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: (Dicke 12.28%) (e171-il)
Reynolds number: 500,000
Max Cl/Cd: 65.35 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e171-il-500000.txt
Download as CSV file: xf-e171-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: (Dicke 12.28%)                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.8400   0.07962   0.07676  -0.0230   1.0000   0.0096
 -13.500  -0.8686   0.07111   0.06811  -0.0276   1.0000   0.0094
 -13.250  -0.8849   0.06530   0.06214  -0.0310   1.0000   0.0094
 -13.000  -0.9058   0.05926   0.05593  -0.0338   1.0000   0.0093
 -12.750  -0.9224   0.05429   0.05079  -0.0356   1.0000   0.0093
 -12.500  -0.9353   0.05023   0.04654  -0.0366   1.0000   0.0094
 -12.250  -0.9491   0.04626   0.04237  -0.0369   1.0000   0.0094
 -12.000  -0.9605   0.04275   0.03865  -0.0365   1.0000   0.0093
 -11.750  -0.9690   0.03986   0.03554  -0.0354   1.0000   0.0094
 -11.500  -0.9663   0.03913   0.03467  -0.0341   1.0000   0.0096
 -11.250  -0.9732   0.03679   0.03210  -0.0317   1.0000   0.0097
 -11.000  -0.9732   0.03528   0.03044  -0.0292   1.0000   0.0097
 -10.750  -0.9794   0.03157   0.02641  -0.0260   1.0000   0.0099
 -10.500  -0.9747   0.02911   0.02374  -0.0236   1.0000   0.0099
 -10.250  -0.9674   0.02657   0.02100  -0.0214   1.0000   0.0102
 -10.000  -0.9570   0.02478   0.01911  -0.0195   1.0000   0.0106
  -9.750  -0.9438   0.02353   0.01777  -0.0178   1.0000   0.0108
  -9.500  -0.9295   0.02243   0.01659  -0.0161   1.0000   0.0112
  -9.250  -0.9139   0.02150   0.01559  -0.0145   1.0000   0.0118
  -9.000  -0.8985   0.02047   0.01448  -0.0128   1.0000   0.0124
  -8.750  -0.8820   0.01959   0.01350  -0.0112   1.0000   0.0131
  -8.500  -0.8648   0.01882   0.01264  -0.0096   1.0000   0.0136
  -8.250  -0.8528   0.01756   0.01128  -0.0072   1.0000   0.0144
  -8.000  -0.8393   0.01655   0.01025  -0.0051   1.0000   0.0160
  -7.750  -0.8210   0.01598   0.00965  -0.0036   1.0000   0.0177
  -7.500  -0.8023   0.01546   0.00907  -0.0021   1.0000   0.0191
  -7.250  -0.7893   0.01443   0.00797   0.0004   1.0000   0.0217
  -7.000  -0.7712   0.01386   0.00737   0.0020   1.0000   0.0246
  -6.750  -0.7522   0.01341   0.00687   0.0036   1.0000   0.0273
  -6.500  -0.7357   0.01277   0.00625   0.0055   1.0000   0.0339
  -6.250  -0.7174   0.01219   0.00572   0.0071   0.9996   0.0453
  -6.000  -0.6806   0.01132   0.00508   0.0044   0.9934   0.0855
  -5.750  -0.6451   0.01055   0.00456   0.0021   0.9849   0.1358
  -5.500  -0.6113   0.00983   0.00410   0.0002   0.9731   0.1934
  -5.250  -0.5769   0.00912   0.00367  -0.0018   0.9581   0.2582
  -5.000  -0.5424   0.00839   0.00325  -0.0038   0.9394   0.3362
  -4.750  -0.5117   0.00783   0.00294  -0.0047   0.9149   0.4129
  -4.500  -0.4860   0.00757   0.00278  -0.0042   0.8886   0.4672
  -4.250  -0.4610   0.00749   0.00268  -0.0035   0.8658   0.4981
  -4.000  -0.4354   0.00747   0.00258  -0.0030   0.8458   0.5195
  -3.750  -0.4093   0.00747   0.00248  -0.0025   0.8286   0.5359
  -3.500  -0.3832   0.00746   0.00242  -0.0020   0.8133   0.5523
  -3.250  -0.3566   0.00746   0.00235  -0.0017   0.7994   0.5659
  -3.000  -0.3298   0.00747   0.00229  -0.0014   0.7867   0.5774
  -2.750  -0.3029   0.00746   0.00223  -0.0012   0.7750   0.5879
  -2.500  -0.2758   0.00746   0.00217  -0.0010   0.7645   0.5979
  -2.250  -0.2484   0.00749   0.00212  -0.0008   0.7544   0.6078
  -2.000  -0.2211   0.00746   0.00208  -0.0006   0.7445   0.6163
  -1.750  -0.1937   0.00747   0.00204  -0.0005   0.7358   0.6252
  -1.500  -0.1661   0.00747   0.00201  -0.0004   0.7270   0.6340
  -1.250  -0.1385   0.00746   0.00198  -0.0003   0.7188   0.6417
  -1.000  -0.1109   0.00749   0.00195  -0.0002   0.7111   0.6500
  -0.750  -0.0832   0.00746   0.00195  -0.0002   0.7031   0.6574
  -0.250  -0.0278   0.00746   0.00194   0.0000   0.6883   0.6734
   0.000   0.0000   0.00749   0.00192   0.0000   0.6813   0.6813
   0.250   0.0277   0.00746   0.00194   0.0001   0.6734   0.6883
   0.750   0.0832   0.00746   0.00195   0.0002   0.6574   0.7031
   1.000   0.1108   0.00749   0.00195   0.0002   0.6500   0.7110
   1.250   0.1385   0.00746   0.00199   0.0003   0.6417   0.7188
   1.500   0.1661   0.00747   0.00201   0.0004   0.6340   0.7270
   1.750   0.1936   0.00747   0.00204   0.0005   0.6252   0.7358
   2.000   0.2211   0.00746   0.00208   0.0006   0.6163   0.7445
   2.250   0.2484   0.00749   0.00212   0.0008   0.6078   0.7544
   2.500   0.2758   0.00746   0.00217   0.0010   0.5979   0.7645
   2.750   0.3029   0.00746   0.00223   0.0012   0.5879   0.7751
   3.000   0.3298   0.00747   0.00229   0.0014   0.5776   0.7867
   3.250   0.3566   0.00746   0.00235   0.0017   0.5660   0.7994
   3.500   0.3832   0.00746   0.00242   0.0020   0.5524   0.8133
   3.750   0.4093   0.00747   0.00248   0.0025   0.5361   0.8287
   4.000   0.4353   0.00747   0.00258   0.0030   0.5196   0.8458
   4.250   0.4609   0.00749   0.00268   0.0036   0.4977   0.8658
   4.500   0.4860   0.00757   0.00278   0.0042   0.4672   0.8886
   4.750   0.5117   0.00783   0.00294   0.0047   0.4127   0.9150
   5.000   0.5424   0.00839   0.00325   0.0038   0.3366   0.9395
   5.250   0.5771   0.00911   0.00367   0.0018   0.2588   0.9581
   5.500   0.6114   0.00983   0.00410  -0.0002   0.1931   0.9731
   5.750   0.6452   0.01056   0.00456  -0.0021   0.1347   0.9849
   6.000   0.6807   0.01131   0.00508  -0.0044   0.0857   0.9934
   6.250   0.7177   0.01219   0.00572  -0.0071   0.0454   0.9996
   6.500   0.7356   0.01277   0.00625  -0.0055   0.0339   1.0000
   6.750   0.7521   0.01342   0.00687  -0.0036   0.0273   1.0000
   7.000   0.7712   0.01387   0.00737  -0.0020   0.0245   1.0000
   7.250   0.7893   0.01442   0.00796  -0.0004   0.0217   1.0000
   7.500   0.8020   0.01548   0.00908   0.0021   0.0192   1.0000
   7.750   0.8212   0.01596   0.00963   0.0035   0.0176   1.0000
   8.000   0.8395   0.01654   0.01023   0.0050   0.0159   1.0000
   8.250   0.8539   0.01747   0.01118   0.0070   0.0146   1.0000
   8.500   0.8647   0.01884   0.01265   0.0096   0.0136   1.0000
   8.750   0.8820   0.01962   0.01352   0.0112   0.0131   1.0000
   9.000   0.8984   0.02051   0.01452   0.0128   0.0125   1.0000
   9.250   0.9142   0.02146   0.01555   0.0144   0.0118   1.0000
   9.500   0.9297   0.02242   0.01658   0.0161   0.0112   1.0000
   9.750   0.9440   0.02358   0.01783   0.0178   0.0109   1.0000
  10.000   0.9568   0.02479   0.01909   0.0195   0.0104   1.0000
  10.250   0.9679   0.02648   0.02091   0.0214   0.0102   1.0000
  10.500   0.9721   0.03015   0.02485   0.0236   0.0098   1.0000
  10.750   0.9791   0.03176   0.02661   0.0260   0.0098   1.0000
  11.000   0.9751   0.03504   0.03018   0.0290   0.0098   1.0000
  11.250   0.9712   0.03699   0.03233   0.0319   0.0097   1.0000
  11.500   0.9688   0.03871   0.03422   0.0340   0.0096   1.0000
  11.750   0.9679   0.04005   0.03576   0.0354   0.0094   1.0000
  12.000   0.9562   0.04353   0.03946   0.0365   0.0094   1.0000
  12.250   0.9527   0.04580   0.04189   0.0368   0.0092   1.0000
  12.500   0.9391   0.04974   0.04605   0.0366   0.0092   1.0000
  12.750   0.9293   0.05340   0.04987   0.0356   0.0091   1.0000
  13.000   0.9060   0.05933   0.05602   0.0336   0.0093   1.0000
  13.250   0.8938   0.06403   0.06087   0.0312   0.0092   1.0000
  13.500   0.8634   0.07215   0.06916   0.0271   0.0095   1.0000
  13.750   0.8548   0.07727   0.07443   0.0235   0.0092   1.0000
  14.000   0.8295   0.08610   0.08341   0.0179   0.0094   1.0000
  14.250   0.7684   0.10694   0.10460   0.0048   0.0109   1.0000
  14.500   0.7617   0.11368   0.11136   0.0009   0.0106   1.0000
  14.750   0.7504   0.12185   0.11956  -0.0035   0.0103   1.0000
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