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E214 (11.1%) (e214-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: E214 (11.1%) (e214-il)
Reynolds number: 500,000
Max Cl/Cd: 121.58 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e214-il-500000.txt
Download as CSV file: xf-e214-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2527   0.09782   0.09573  -0.0498   0.9929   0.0205
  -9.750  -0.2483   0.09277   0.09069  -0.0527   0.9910   0.0205
  -9.500  -0.2500   0.08633   0.08427  -0.0548   0.9894   0.0212
  -9.250  -0.2385   0.08294   0.08087  -0.0567   0.9878   0.0217
  -9.000  -0.2263   0.07941   0.07734  -0.0590   0.9863   0.0225
  -8.750  -0.2169   0.07487   0.07281  -0.0623   0.9850   0.0232
  -8.500  -0.3373   0.08177   0.07965  -0.0573   0.9888   0.0212
  -8.250  -0.3208   0.07928   0.07716  -0.0601   0.9865   0.0219
  -8.000  -0.3038   0.07574   0.07362  -0.0649   0.9845   0.0227
  -7.750  -0.2981   0.07130   0.06919  -0.0694   0.9782   0.0233
  -7.500  -0.2824   0.06430   0.06220  -0.0801   0.9732   0.0243
  -7.250  -0.2690   0.05210   0.04986  -0.0992   0.9637   0.0248
  -7.000  -0.2379   0.04257   0.03962  -0.1134   0.9596   0.0274
  -6.250  -0.1716   0.02068   0.01584  -0.1246   0.9470   0.0211
  -6.000  -0.1356   0.01827   0.01311  -0.1271   0.9461   0.0212
  -5.750  -0.1135   0.01674   0.01142  -0.1263   0.9397   0.0218
  -5.500  -0.0794   0.01574   0.01035  -0.1280   0.9375   0.0232
  -5.250  -0.0434   0.01453   0.00902  -0.1298   0.9359   0.0240
  -5.000  -0.0061   0.01343   0.00780  -0.1318   0.9346   0.0246
  -4.750   0.0324   0.01252   0.00681  -0.1341   0.9333   0.0255
  -4.500   0.0627   0.01190   0.00611  -0.1347   0.9285   0.0266
  -4.250   0.0947   0.01126   0.00541  -0.1356   0.9238   0.0277
  -4.000   0.1315   0.01035   0.00443  -0.1376   0.9207   0.0298
  -3.750   0.1674   0.00986   0.00389  -0.1394   0.9168   0.0323
  -3.500   0.1966   0.00952   0.00350  -0.1395   0.9091   0.0352
  -3.250   0.2334   0.00904   0.00301  -0.1414   0.9045   0.0486
  -3.000   0.2613   0.00838   0.00271  -0.1418   0.8953   0.1406
  -2.750   0.2950   0.00790   0.00247  -0.1433   0.8884   0.2263
  -2.500   0.3236   0.00745   0.00231  -0.1437   0.8784   0.3265
  -2.250   0.3525   0.00703   0.00224  -0.1442   0.8681   0.4535
  -2.000   0.3824   0.00689   0.00221  -0.1446   0.8580   0.5231
  -1.750   0.4117   0.00685   0.00215  -0.1447   0.8469   0.5593
  -1.500   0.4392   0.00683   0.00213  -0.1445   0.8342   0.5865
  -1.250   0.4669   0.00683   0.00210  -0.1443   0.8212   0.6082
  -1.000   0.4943   0.00685   0.00209  -0.1441   0.8080   0.6274
  -0.750   0.5217   0.00688   0.00207  -0.1439   0.7948   0.6420
  -0.500   0.5488   0.00693   0.00206  -0.1436   0.7814   0.6557
  -0.250   0.5757   0.00698   0.00207  -0.1433   0.7682   0.6694
   0.000   0.6024   0.00704   0.00209  -0.1430   0.7552   0.6835
   0.250   0.6290   0.00712   0.00212  -0.1426   0.7427   0.6975
   0.500   0.6555   0.00719   0.00216  -0.1422   0.7304   0.7116
   0.750   0.6817   0.00726   0.00221  -0.1418   0.7181   0.7262
   1.000   0.7078   0.00732   0.00228  -0.1414   0.7062   0.7417
   1.250   0.7337   0.00738   0.00235  -0.1409   0.6946   0.7583
   1.500   0.7594   0.00745   0.00242  -0.1404   0.6833   0.7763
   1.750   0.7848   0.00753   0.00249  -0.1398   0.6720   0.7957
   2.000   0.8096   0.00757   0.00259  -0.1391   0.6601   0.8170
   2.250   0.8336   0.00761   0.00267  -0.1382   0.6483   0.8432
   2.500   0.8555   0.00763   0.00276  -0.1368   0.6369   0.8771
   2.750   0.8731   0.00758   0.00278  -0.1343   0.6259   0.9417
   3.250   0.9291   0.00782   0.00295  -0.1345   0.6010   1.0000
   3.500   0.9552   0.00797   0.00306  -0.1343   0.5879   1.0000
   3.750   0.9809   0.00814   0.00318  -0.1339   0.5742   1.0000
   4.000   1.0063   0.00832   0.00332  -0.1334   0.5600   1.0000
   4.250   1.0315   0.00850   0.00347  -0.1330   0.5460   1.0000
   4.500   1.0565   0.00869   0.00363  -0.1324   0.5317   1.0000
   4.750   1.0810   0.00890   0.00381  -0.1318   0.5161   1.0000
   5.000   1.1049   0.00913   0.00399  -0.1311   0.4993   1.0000
   5.250   1.1283   0.00939   0.00419  -0.1303   0.4815   1.0000
   5.500   1.1520   0.00963   0.00440  -0.1296   0.4630   1.0000
   5.750   1.1750   0.00991   0.00465  -0.1287   0.4430   1.0000
   6.000   1.1970   0.01024   0.00491  -0.1277   0.4217   1.0000
   6.250   1.2183   0.01061   0.00520  -0.1265   0.3961   1.0000
   6.500   1.2388   0.01103   0.00551  -0.1253   0.3680   1.0000
   6.750   1.2583   0.01151   0.00588  -0.1238   0.3379   1.0000
   7.000   1.2768   0.01206   0.00629  -0.1223   0.3059   1.0000
   7.250   1.2949   0.01264   0.00674  -0.1207   0.2737   1.0000
   7.500   1.3110   0.01331   0.00724  -0.1188   0.2392   1.0000
   7.750   1.3251   0.01404   0.00779  -0.1165   0.2049   1.0000
   8.000   1.3382   0.01482   0.00840  -0.1141   0.1709   1.0000
   8.250   1.3502   0.01567   0.00907  -0.1115   0.1395   1.0000
   8.500   1.3627   0.01649   0.00974  -0.1091   0.1135   1.0000
   8.750   1.3760   0.01724   0.01040  -0.1069   0.0943   1.0000
   9.000   1.3892   0.01800   0.01109  -0.1046   0.0781   1.0000
   9.250   1.4021   0.01877   0.01182  -0.1024   0.0654   1.0000
   9.500   1.4149   0.01956   0.01258  -0.1002   0.0549   1.0000
   9.750   1.4270   0.02039   0.01341  -0.0979   0.0460   1.0000
  10.000   1.4380   0.02130   0.01430  -0.0956   0.0375   1.0000
  10.250   1.4474   0.02233   0.01531  -0.0931   0.0291   1.0000
  10.500   1.4543   0.02356   0.01652  -0.0904   0.0211   1.0000
  10.750   1.4591   0.02498   0.01794  -0.0875   0.0158   1.0000
  11.000   1.4653   0.02634   0.01935  -0.0850   0.0131   1.0000
  11.250   1.4687   0.02796   0.02107  -0.0822   0.0117   1.0000
  11.500   1.4759   0.02933   0.02254  -0.0801   0.0108   1.0000
  11.750   1.4817   0.03087   0.02418  -0.0781   0.0102   1.0000
  12.000   1.4855   0.03262   0.02602  -0.0760   0.0096   1.0000
  12.250   1.4844   0.03489   0.02839  -0.0737   0.0091   1.0000
  12.500   1.4771   0.03785   0.03148  -0.0713   0.0087   1.0000
  12.750   1.4798   0.04002   0.03378  -0.0699   0.0085   1.0000
  13.000   1.4814   0.04238   0.03626  -0.0686   0.0083   1.0000
  13.250   1.4815   0.04501   0.03901  -0.0675   0.0081   1.0000
  13.500   1.4808   0.04784   0.04198  -0.0666   0.0079   1.0000
  13.750   1.4793   0.05090   0.04516  -0.0659   0.0077   1.0000
  14.000   1.4774   0.05412   0.04850  -0.0654   0.0075   1.0000
  14.250   1.4755   0.05746   0.05197  -0.0651   0.0074   1.0000
  14.500   1.4732   0.06099   0.05562  -0.0651   0.0072   1.0000
  14.750   1.4707   0.06464   0.05939  -0.0653   0.0071   1.0000
  15.000   1.4680   0.06843   0.06331  -0.0657   0.0069   1.0000
  15.250   1.4642   0.07251   0.06751  -0.0663   0.0068   1.0000
  15.500   1.4599   0.07677   0.07188  -0.0672   0.0066   1.0000
  15.750   1.4540   0.08140   0.07662  -0.0682   0.0065   1.0000
  16.000   1.4467   0.08635   0.08170  -0.0695   0.0064   1.0000
  16.250   1.4379   0.09166   0.08716  -0.0709   0.0063   1.0000
  16.500   1.4280   0.09727   0.09294  -0.0725   0.0062   1.0000
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