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E201 (11.88%) (e201-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: E201 (11.88%) (e201-il)
Reynolds number: 50,000
Max Cl/Cd: 34 at α=9.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e201-il-50000.txt
Download as CSV file: xf-e201-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E201  (11.88%)                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3652   0.11953   0.11251  -0.0282   1.0000   0.2339
  -9.750  -0.3472   0.11463   0.10762  -0.0274   1.0000   0.2416
  -9.500  -0.3686   0.11457   0.10771  -0.0287   1.0000   0.2495
  -9.250  -0.3410   0.10876   0.10187  -0.0274   1.0000   0.2576
  -9.000  -0.3560   0.10745   0.10070  -0.0280   1.0000   0.2656
  -8.750  -0.3384   0.10330   0.09655  -0.0270   1.0000   0.2753
  -8.500  -0.3407   0.10057   0.09392  -0.0268   1.0000   0.2828
  -8.250  -0.3553   0.09957   0.09307  -0.0262   1.0000   0.2939
  -8.000  -0.3346   0.09483   0.08831  -0.0252   1.0000   0.3004
  -7.750  -0.3497   0.09331   0.08696  -0.0242   1.0000   0.3108
  -7.500  -0.3453   0.09061   0.08433  -0.0227   1.0000   0.3222
  -7.250  -0.3385   0.08736   0.08115  -0.0213   1.0000   0.3308
  -7.000  -0.3555   0.08595   0.07993  -0.0189   1.0000   0.3413
  -6.750  -0.3681   0.08466   0.07880  -0.0158   1.0000   0.3527
  -6.250  -0.4992   0.06418   0.05833  -0.0394   1.0000   0.1485
  -6.000  -0.5065   0.05769   0.05133  -0.0419   1.0000   0.1309
  -5.750  -0.5010   0.05422   0.04780  -0.0408   1.0000   0.1268
  -5.500  -0.4956   0.04827   0.04086  -0.0428   1.0000   0.1172
  -5.250  -0.4831   0.04503   0.03738  -0.0423   1.0000   0.1156
  -5.000  -0.4679   0.04187   0.03380  -0.0421   1.0000   0.1144
  -4.750  -0.4499   0.03913   0.03049  -0.0419   1.0000   0.1157
  -4.500  -0.4304   0.03672   0.02757  -0.0416   1.0000   0.1190
  -4.250  -0.4117   0.03497   0.02574  -0.0410   1.0000   0.1240
  -4.000  -0.3904   0.03317   0.02348  -0.0404   1.0000   0.1290
  -3.750  -0.3695   0.03153   0.02165  -0.0397   1.0000   0.1371
  -3.500  -0.3495   0.03029   0.02034  -0.0389   1.0000   0.1539
  -3.250  -0.3289   0.02898   0.01908  -0.0380   1.0000   0.1826
  -3.000  -0.3090   0.02773   0.01815  -0.0373   1.0000   0.2456
  -2.750  -0.2901   0.02656   0.01766  -0.0361   1.0000   0.3493
  -2.500  -0.2729   0.02597   0.01783  -0.0339   0.9992   0.4918
  -2.250  -0.2483   0.02603   0.01842  -0.0319   0.9914   0.6312
  -2.000  -0.2269   0.02621   0.01889  -0.0290   0.9837   0.7369
  -1.750  -0.2116   0.02613   0.01903  -0.0250   0.9755   0.8343
  -1.500  -0.1235   0.02642   0.01899  -0.0373   0.9667   1.0000
  -1.250  -0.0817   0.02692   0.01891  -0.0434   0.9577   1.0000
  -1.000  -0.0518   0.02738   0.01893  -0.0460   0.9485   1.0000
  -0.750  -0.0161   0.02813   0.01930  -0.0492   0.9404   1.0000
  -0.500   0.0163   0.02885   0.01969  -0.0515   0.9318   1.0000
  -0.250   0.0447   0.02958   0.02013  -0.0531   0.9237   1.0000
   0.000   0.0804   0.03044   0.02073  -0.0558   0.9158   1.0000
   0.250   0.1024   0.03115   0.02125  -0.0562   0.9076   1.0000
   0.500   0.1398   0.03210   0.02198  -0.0590   0.9002   1.0000
   0.750   0.1567   0.03283   0.02257  -0.0585   0.8920   1.0000
   1.000   0.1934   0.03383   0.02341  -0.0611   0.8847   1.0000
   1.250   0.2078   0.03464   0.02411  -0.0603   0.8768   1.0000
   1.500   0.2426   0.03567   0.02502  -0.0626   0.8696   1.0000
   1.750   0.2561   0.03657   0.02584  -0.0616   0.8619   1.0000
   2.000   0.2897   0.03766   0.02684  -0.0636   0.8544   1.0000
   2.250   0.3020   0.03866   0.02779  -0.0626   0.8470   1.0000
   2.500   0.3345   0.03979   0.02887  -0.0644   0.8394   1.0000
   2.750   0.3462   0.04088   0.02992  -0.0634   0.8319   1.0000
   3.000   0.3761   0.04206   0.03109  -0.0648   0.8238   1.0000
   3.250   0.3896   0.04325   0.03227  -0.0641   0.8161   1.0000
   3.500   0.4146   0.04448   0.03350  -0.0648   0.8074   1.0000
   3.750   0.4355   0.04573   0.03476  -0.0650   0.7990   1.0000
   4.000   0.4521   0.04706   0.03610  -0.0647   0.7900   1.0000
   4.250   0.4860   0.04832   0.03743  -0.0664   0.7801   1.0000
   4.500   0.4951   0.04971   0.03884  -0.0652   0.7705   1.0000
   4.750   0.5141   0.05111   0.04029  -0.0652   0.7599   1.0000
   5.000   0.5416   0.05242   0.04168  -0.0659   0.7484   1.0000
   5.250   0.5749   0.05364   0.04301  -0.0671   0.7359   1.0000
   5.500   0.5855   0.05513   0.04458  -0.0661   0.7237   1.0000
   5.750   0.6021   0.05660   0.04613  -0.0657   0.7105   1.0000
   6.000   0.6237   0.05795   0.04758  -0.0655   0.6959   1.0000
   6.250   0.6473   0.05922   0.04901  -0.0654   0.6806   1.0000
   6.500   0.6742   0.06034   0.05027  -0.0654   0.6646   1.0000
   6.750   0.7118   0.06094   0.05106  -0.0658   0.6474   1.0000
   7.000   0.7258   0.06234   0.05259  -0.0647   0.6298   1.0000
   7.250   0.7399   0.06373   0.05413  -0.0635   0.6113   1.0000
   7.500   0.7684   0.06432   0.05492  -0.0628   0.5921   1.0000
   7.750   0.8225   0.06302   0.05395  -0.0625   0.5725   1.0000
   8.000   0.8215   0.06509   0.05615  -0.0605   0.5512   1.0000
   8.250   0.8891   0.06152   0.05302  -0.0591   0.5298   1.0000
   8.500   0.8956   0.06278   0.05442  -0.0568   0.5064   1.0000
   8.750   1.1024   0.04151   0.03438  -0.0537   0.4658   1.0000
   9.000   1.1595   0.03533   0.02826  -0.0499   0.4065   1.0000
   9.250   1.1690   0.03438   0.02694  -0.0447   0.3472   1.0000
   9.500   1.1677   0.03542   0.02740  -0.0397   0.2935   1.0000
   9.750   1.1630   0.03744   0.02893  -0.0352   0.2488   1.0000
  10.000   1.1605   0.03986   0.03089  -0.0315   0.2091   1.0000
  10.250   1.1562   0.04239   0.03321  -0.0282   0.1780   1.0000
  10.500   1.1552   0.04508   0.03567  -0.0255   0.1499   1.0000
  10.750   1.1668   0.04804   0.03841  -0.0238   0.1245   1.0000
  11.000   1.1903   0.05134   0.04172  -0.0230   0.1062   1.0000
  11.250   1.2113   0.05494   0.04553  -0.0224   0.0964   1.0000
  11.500   1.2373   0.05894   0.04954  -0.0226   0.0883   1.0000
  11.750   1.2346   0.06247   0.05353  -0.0202   0.0868   1.0000
  12.000   1.2272   0.06625   0.05771  -0.0179   0.0857   1.0000
  12.250   1.2151   0.07024   0.06206  -0.0160   0.0852   1.0000
  12.500   1.1987   0.07449   0.06663  -0.0146   0.0850   1.0000
  12.750   1.1792   0.07910   0.07153  -0.0139   0.0852   1.0000
  13.000   1.1574   0.08418   0.07686  -0.0140   0.0857   1.0000
  13.250   1.1338   0.08982   0.08272  -0.0150   0.0863   1.0000
  13.500   1.1088   0.09612   0.08921  -0.0170   0.0871   1.0000
  13.750   1.0852   0.10294   0.09618  -0.0196   0.0879   1.0000
  14.000   1.0644   0.11013   0.10347  -0.0227   0.0886   1.0000
  14.250   0.9697   0.13170   0.12519  -0.0389   0.1005   1.0000
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