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(Dicke 12.28%) (e171-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: (Dicke 12.28%) (e171-il)
Reynolds number: 50,000
Max Cl/Cd: 29.17 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e171-il-50000.txt
Download as CSV file: xf-e171-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.6299   0.11360   0.10665  -0.0033   1.0000   0.1464
 -11.000  -0.6794   0.09901   0.09233  -0.0157   1.0000   0.1258
 -10.750  -0.7445   0.08553   0.07884  -0.0275   1.0000   0.1104
 -10.500  -0.7530   0.08010   0.07340  -0.0288   1.0000   0.1092
 -10.250  -0.7713   0.07505   0.06831  -0.0300   1.0000   0.1078
 -10.000  -0.7931   0.07053   0.06371  -0.0296   1.0000   0.1062
  -9.750  -0.8149   0.06613   0.05913  -0.0285   1.0000   0.1039
  -9.500  -0.8319   0.06179   0.05449  -0.0270   1.0000   0.1029
  -9.250  -0.8407   0.05766   0.05003  -0.0253   1.0000   0.1025
  -9.000  -0.8426   0.05378   0.04579  -0.0235   1.0000   0.1035
  -8.750  -0.8400   0.04996   0.04156  -0.0216   1.0000   0.1044
  -8.500  -0.8327   0.04622   0.03736  -0.0196   1.0000   0.1056
  -8.250  -0.8225   0.04290   0.03349  -0.0176   1.0000   0.1088
  -8.000  -0.8054   0.03991   0.03037  -0.0164   1.0000   0.1166
  -7.750  -0.7881   0.03715   0.02708  -0.0146   1.0000   0.1241
  -7.500  -0.7642   0.03439   0.02423  -0.0137   1.0000   0.1371
  -7.250  -0.7404   0.03186   0.02190  -0.0127   1.0000   0.1579
  -7.000  -0.7200   0.02950   0.01973  -0.0111   1.0000   0.1902
  -6.750  -0.7068   0.02718   0.01789  -0.0086   1.0000   0.2410
  -6.500  -0.7016   0.02499   0.01647  -0.0049   1.0000   0.3177
  -6.250  -0.6987   0.02394   0.01635   0.0005   1.0000   0.4197
  -6.000  -0.6884   0.02481   0.01760   0.0064   1.0000   0.5060
  -5.750  -0.6708   0.02630   0.01909   0.0118   1.0000   0.5649
  -5.500  -0.6468   0.02796   0.02068   0.0167   1.0000   0.6090
  -5.250  -0.6152   0.02971   0.02226   0.0210   1.0000   0.6449
  -5.000  -0.5885   0.03062   0.02298   0.0247   1.0000   0.6767
  -4.750  -0.5568   0.03141   0.02352   0.0274   1.0000   0.7055
  -4.500  -0.5199   0.03198   0.02384   0.0289   1.0000   0.7320
  -4.250  -0.4887   0.03202   0.02367   0.0301   1.0000   0.7567
  -4.000  -0.4575   0.03188   0.02333   0.0306   1.0000   0.7799
  -3.750  -0.4078   0.03185   0.02300   0.0282   1.0000   0.8015
  -3.500  -0.3687   0.03145   0.02241   0.0264   1.0000   0.8218
  -3.250  -0.3478   0.03084   0.02168   0.0270   1.0000   0.8403
  -3.000  -0.2951   0.03035   0.02098   0.0224   1.0000   0.8573
  -2.750  -0.2582   0.02976   0.02028   0.0199   1.0000   0.8733
  -2.500  -0.2282   0.02920   0.01964   0.0182   1.0000   0.8885
  -2.250  -0.2020   0.02869   0.01906   0.0169   1.0000   0.9032
  -2.000  -0.1783   0.02827   0.01860   0.0158   1.0000   0.9173
  -1.750  -0.1538   0.02791   0.01819   0.0142   1.0000   0.9312
  -1.500  -0.1278   0.02760   0.01782   0.0121   1.0000   0.9449
  -1.250  -0.0988   0.02732   0.01750   0.0093   1.0000   0.9583
  -1.000  -0.0657   0.02705   0.01720   0.0055   1.0000   0.9717
  -0.750  -0.0277   0.02678   0.01691   0.0007   1.0000   0.9849
  -0.500   0.0160   0.02649   0.01660  -0.0054   1.0000   0.9983
  -0.250   0.0116   0.02659   0.01671  -0.0033   1.0000   1.0000
   0.000   0.0000   0.02664   0.01677   0.0000   1.0000   1.0000
   0.250  -0.0117   0.02659   0.01671   0.0033   1.0000   1.0000
   0.500  -0.0160   0.02648   0.01660   0.0054   0.9983   1.0000
   0.750   0.0275   0.02677   0.01690  -0.0006   0.9849   1.0000
   1.000   0.0655   0.02704   0.01720  -0.0055   0.9717   1.0000
   1.250   0.0983   0.02730   0.01749  -0.0092   0.9584   1.0000
   1.500   0.1271   0.02758   0.01781  -0.0120   0.9450   1.0000
   1.750   0.1535   0.02790   0.01818  -0.0141   0.9313   1.0000
   2.000   0.1776   0.02826   0.01858  -0.0157   0.9174   1.0000
   2.250   0.2021   0.02868   0.01906  -0.0170   0.9032   1.0000
   2.500   0.2275   0.02919   0.01961  -0.0181   0.8887   1.0000
   2.750   0.2581   0.02975   0.02027  -0.0199   0.8733   1.0000
   3.000   0.2950   0.03034   0.02097  -0.0224   0.8573   1.0000
   3.250   0.3473   0.03084   0.02170  -0.0269   0.8404   1.0000
   3.500   0.3689   0.03144   0.02240  -0.0265   0.8218   1.0000
   3.750   0.4075   0.03185   0.02300  -0.0282   0.8016   1.0000
   4.000   0.4580   0.03186   0.02331  -0.0307   0.7800   1.0000
   4.250   0.4883   0.03202   0.02367  -0.0300   0.7568   1.0000
   4.500   0.5200   0.03196   0.02383  -0.0289   0.7320   1.0000
   4.750   0.5568   0.03140   0.02351  -0.0274   0.7055   1.0000
   5.000   0.5887   0.03061   0.02298  -0.0247   0.6768   1.0000
   5.250   0.6152   0.02970   0.02226  -0.0210   0.6449   1.0000
   5.500   0.6468   0.02796   0.02067  -0.0167   0.6090   1.0000
   5.750   0.6708   0.02630   0.01908  -0.0118   0.5649   1.0000
   6.000   0.6884   0.02480   0.01759  -0.0064   0.5061   1.0000
   6.250   0.6987   0.02395   0.01635  -0.0005   0.4196   1.0000
   6.500   0.7016   0.02499   0.01646   0.0049   0.3178   1.0000
   6.750   0.7068   0.02718   0.01789   0.0086   0.2408   1.0000
   7.000   0.7200   0.02949   0.01973   0.0111   0.1901   1.0000
   7.250   0.7404   0.03185   0.02189   0.0127   0.1579   1.0000
   7.500   0.7643   0.03439   0.02423   0.0137   0.1371   1.0000
   7.750   0.7881   0.03717   0.02710   0.0146   0.1241   1.0000
   8.000   0.8055   0.03990   0.03035   0.0164   0.1164   1.0000
   8.250   0.8227   0.04289   0.03348   0.0176   0.1088   1.0000
   8.500   0.8328   0.04622   0.03736   0.0196   0.1056   1.0000
   8.750   0.8401   0.04996   0.04156   0.0216   0.1043   1.0000
   9.000   0.8427   0.05381   0.04582   0.0235   0.1036   1.0000
   9.250   0.8406   0.05768   0.05005   0.0253   0.1027   1.0000
   9.500   0.8327   0.06173   0.05442   0.0270   0.1025   1.0000
   9.750   0.8149   0.06619   0.05918   0.0285   0.1043   1.0000
  10.000   0.7937   0.07061   0.06378   0.0295   0.1064   1.0000
  10.250   0.7732   0.07502   0.06828   0.0299   0.1080   1.0000
  10.500   0.7545   0.08017   0.07347   0.0288   0.1093   1.0000
  10.750   0.7462   0.08555   0.07886   0.0275   0.1105   1.0000
  11.000   0.5546   0.09933   0.09295   0.0141   0.1400   1.0000
  11.250   0.5608   0.10386   0.09746   0.0141   0.1382   1.0000
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