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E214 (11.1%) (e214-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: E214 (11.1%) (e214-il)
Reynolds number: 1,000,000
Max Cl/Cd: 145.91 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e214-il-1000000.txt
Download as CSV file: xf-e214-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E214  (11.1%)                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2877   0.08234   0.08073  -0.0669   0.9878   0.0125
  -8.750  -0.2969   0.02770   0.02608  -0.1028   0.9748   0.0106
  -8.500  -0.3233   0.01538   0.01308  -0.1214   0.9637   0.0103
  -8.250  -0.3069   0.01024   0.00736  -0.1267   0.9612   0.0106
  -8.000  -0.2782   0.00827   0.00504  -0.1296   0.9602   0.0110
  -7.750  -0.2522   0.00555   0.00180  -0.1327   0.9590   0.0117
  -7.500  -0.2472   0.01653   0.01248  -0.1355   0.9592   0.0120
  -7.250  -0.2279   0.01600   0.01191  -0.1342   0.9531   0.0125
  -7.000  -0.1958   0.01551   0.01138  -0.1355   0.9511   0.0132
  -6.750  -0.1623   0.01443   0.01015  -0.1372   0.9494   0.0137
  -6.500  -0.1289   0.01346   0.00903  -0.1387   0.9476   0.0142
  -6.250  -0.0939   0.01263   0.00808  -0.1405   0.9460   0.0147
  -6.000  -0.0686   0.01223   0.00760  -0.1400   0.9401   0.0151
  -5.750  -0.0385   0.01081   0.00603  -0.1410   0.9359   0.0159
  -5.500  -0.0039   0.01005   0.00524  -0.1428   0.9329   0.0170
  -5.250   0.0234   0.00961   0.00476  -0.1428   0.9263   0.0177
  -5.000   0.0552   0.00913   0.00421  -0.1438   0.9208   0.0182
  -4.750   0.0852   0.00874   0.00375  -0.1444   0.9145   0.0189
  -4.500   0.1149   0.00840   0.00335  -0.1448   0.9071   0.0196
  -4.250   0.1440   0.00815   0.00304  -0.1451   0.8994   0.0203
  -4.000   0.1734   0.00776   0.00255  -0.1455   0.8911   0.0217
  -3.750   0.2013   0.00750   0.00222  -0.1455   0.8817   0.0234
  -3.500   0.2299   0.00733   0.00199  -0.1456   0.8723   0.0252
  -3.250   0.2581   0.00719   0.00179  -0.1456   0.8616   0.0273
  -3.000   0.2854   0.00690   0.00158  -0.1456   0.8497   0.0594
  -2.750   0.3127   0.00658   0.00143  -0.1457   0.8371   0.1221
  -2.500   0.3399   0.00634   0.00133  -0.1457   0.8236   0.1821
  -2.250   0.3668   0.00613   0.00124  -0.1456   0.8094   0.2484
  -2.000   0.3936   0.00588   0.00118  -0.1456   0.7949   0.3329
  -1.750   0.4202   0.00564   0.00115  -0.1456   0.7803   0.4335
  -1.500   0.4468   0.00557   0.00117  -0.1454   0.7658   0.4949
  -1.250   0.4734   0.00559   0.00118  -0.1451   0.7518   0.5291
  -1.000   0.5001   0.00562   0.00121  -0.1448   0.7385   0.5543
  -0.750   0.5268   0.00568   0.00123  -0.1445   0.7257   0.5766
  -0.500   0.5534   0.00574   0.00126  -0.1442   0.7134   0.5924
  -0.250   0.5800   0.00581   0.00129  -0.1439   0.7013   0.6047
   0.000   0.6070   0.00586   0.00132  -0.1437   0.6896   0.6166
   0.250   0.6339   0.00592   0.00136  -0.1434   0.6782   0.6286
   0.500   0.6606   0.00598   0.00140  -0.1432   0.6673   0.6410
   0.750   0.6872   0.00606   0.00145  -0.1429   0.6562   0.6536
   1.000   0.7139   0.00613   0.00151  -0.1427   0.6449   0.6664
   1.250   0.7407   0.00619   0.00157  -0.1424   0.6337   0.6800
   1.500   0.7673   0.00626   0.00163  -0.1422   0.6223   0.6943
   1.750   0.7936   0.00634   0.00171  -0.1418   0.6109   0.7101
   2.250   0.8462   0.00648   0.00188  -0.1412   0.5873   0.7452
   2.500   0.8724   0.00655   0.00197  -0.1409   0.5753   0.7640
   2.750   0.8982   0.00664   0.00207  -0.1405   0.5626   0.7849
   3.000   0.9236   0.00672   0.00218  -0.1399   0.5491   0.8091
   3.250   0.9483   0.00680   0.00230  -0.1393   0.5350   0.8381
   3.500   0.9715   0.00686   0.00242  -0.1383   0.5216   0.8767
   3.750   0.9902   0.00681   0.00249  -0.1361   0.5088   0.9671
   4.000   1.0170   0.00697   0.00260  -0.1360   0.4934   1.0000
   4.250   1.0426   0.00716   0.00273  -0.1356   0.4765   1.0000
   4.500   1.0679   0.00737   0.00288  -0.1352   0.4586   1.0000
   4.750   1.0927   0.00761   0.00305  -0.1347   0.4400   1.0000
   5.000   1.1174   0.00786   0.00322  -0.1342   0.4212   1.0000
   5.250   1.1417   0.00812   0.00341  -0.1336   0.3997   1.0000
   5.500   1.1654   0.00843   0.00363  -0.1329   0.3780   1.0000
   5.750   1.1880   0.00881   0.00389  -0.1320   0.3490   1.0000
   6.000   1.2101   0.00922   0.00416  -0.1311   0.3191   1.0000
   6.250   1.2316   0.00966   0.00447  -0.1301   0.2886   1.0000
   6.500   1.2528   0.01013   0.00480  -0.1290   0.2594   1.0000
   6.750   1.2724   0.01069   0.00519  -0.1276   0.2252   1.0000
   7.000   1.2904   0.01135   0.00565  -0.1260   0.1876   1.0000
   7.250   1.3082   0.01200   0.00611  -0.1244   0.1543   1.0000
   7.500   1.3258   0.01264   0.00659  -0.1227   0.1264   1.0000
   7.750   1.3440   0.01319   0.00703  -0.1212   0.1058   1.0000
   8.000   1.3605   0.01376   0.00751  -0.1193   0.0877   1.0000
   8.250   1.3767   0.01431   0.00798  -0.1173   0.0727   1.0000
   8.500   1.3927   0.01485   0.00846  -0.1153   0.0603   1.0000
   8.750   1.4083   0.01542   0.00898  -0.1133   0.0491   1.0000
   9.000   1.4234   0.01601   0.00952  -0.1112   0.0401   1.0000
   9.250   1.4390   0.01657   0.01006  -0.1092   0.0333   1.0000
   9.500   1.4541   0.01717   0.01065  -0.1072   0.0271   1.0000
   9.750   1.4675   0.01785   0.01132  -0.1050   0.0210   1.0000
  10.000   1.4782   0.01871   0.01214  -0.1024   0.0138   1.0000
  10.250   1.4873   0.01969   0.01309  -0.0996   0.0091   1.0000
  10.500   1.4996   0.02048   0.01394  -0.0974   0.0078   1.0000
  10.750   1.5109   0.02134   0.01484  -0.0951   0.0069   1.0000
  11.000   1.5185   0.02248   0.01605  -0.0923   0.0061   1.0000
  11.250   1.5298   0.02337   0.01703  -0.0902   0.0059   1.0000
  11.500   1.5403   0.02434   0.01807  -0.0881   0.0056   1.0000
  11.750   1.5496   0.02542   0.01923  -0.0860   0.0053   1.0000
  12.000   1.5578   0.02662   0.02051  -0.0838   0.0051   1.0000
  12.250   1.5652   0.02792   0.02188  -0.0817   0.0049   1.0000
  12.500   1.5699   0.02947   0.02351  -0.0795   0.0046   1.0000
  12.750   1.5711   0.03137   0.02552  -0.0771   0.0044   1.0000
  13.000   1.5646   0.03406   0.02836  -0.0744   0.0042   1.0000
  13.250   1.5703   0.03577   0.03015  -0.0729   0.0041   1.0000
  13.500   1.5738   0.03775   0.03222  -0.0715   0.0040   1.0000
  13.750   1.5758   0.03998   0.03456  -0.0701   0.0040   1.0000
  14.000   1.5766   0.04241   0.03711  -0.0689   0.0039   1.0000
  14.250   1.5772   0.04499   0.03979  -0.0680   0.0038   1.0000
  14.500   1.5755   0.04796   0.04287  -0.0672   0.0038   1.0000
  14.750   1.5738   0.05106   0.04609  -0.0667   0.0037   1.0000
  15.000   1.5711   0.05441   0.04956  -0.0664   0.0037   1.0000
  15.250   1.5670   0.05809   0.05336  -0.0664   0.0036   1.0000
  15.500   1.5628   0.06195   0.05734  -0.0666   0.0036   1.0000
  15.750   1.5575   0.06608   0.06159  -0.0671   0.0036   1.0000
  16.000   1.5512   0.07054   0.06618  -0.0679   0.0035   1.0000
  16.250   1.5446   0.07521   0.07097  -0.0690   0.0035   1.0000
  16.500   1.5369   0.08021   0.07610  -0.0703   0.0034   1.0000
  16.750   1.5286   0.08546   0.08148  -0.0720   0.0034   1.0000
  17.000   1.5200   0.09093   0.08707  -0.0739   0.0034   1.0000
  17.250   1.5105   0.09672   0.09299  -0.0761   0.0034   1.0000
  17.500   1.5009   0.10266   0.09907  -0.0786   0.0033   1.0000
  17.750   1.4902   0.10892   0.10545  -0.0813   0.0033   1.0000
  18.000   1.4802   0.11520   0.11186  -0.0843   0.0033   1.0000
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