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E214 (11.1%) (e214-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: E214 (11.1%) (e214-il)
Reynolds number: 100,000
Max Cl/Cd: 63.16 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e214-il-100000-n5.txt
Download as CSV file: xf-e214-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3558   0.10660   0.10174  -0.0391   1.0000   0.0376
  -9.000  -0.3573   0.10369   0.09888  -0.0383   1.0000   0.0356
  -8.750  -0.3631   0.10055   0.09581  -0.0379   1.0000   0.0345
  -8.500  -0.3704   0.09757   0.09290  -0.0374   1.0000   0.0341
  -8.000  -0.4125   0.08838   0.08393  -0.0387   1.0000   0.0299
  -7.750  -0.4240   0.08523   0.08086  -0.0387   0.9989   0.0300
  -7.500  -0.4138   0.07847   0.07410  -0.0471   0.9923   0.0300
  -7.250  -0.3982   0.06911   0.06467  -0.0603   0.9846   0.0299
  -7.000  -0.3854   0.06131   0.05667  -0.0697   0.9761   0.0297
  -6.750  -0.3683   0.05413   0.04919  -0.0779   0.9693   0.0294
  -6.500  -0.3487   0.04759   0.04222  -0.0844   0.9621   0.0293
  -6.250  -0.3227   0.04184   0.03591  -0.0898   0.9566   0.0293
  -6.000  -0.2954   0.03717   0.03058  -0.0934   0.9506   0.0295
  -5.750  -0.2615   0.03335   0.02614  -0.0972   0.9470   0.0307
  -5.500  -0.2342   0.03158   0.02421  -0.0986   0.9410   0.0327
  -5.250  -0.2015   0.02932   0.02152  -0.1006   0.9363   0.0339
  -5.000  -0.1650   0.02716   0.01894  -0.1028   0.9332   0.0348
  -4.750  -0.1363   0.02559   0.01707  -0.1033   0.9269   0.0358
  -4.500  -0.1030   0.02418   0.01541  -0.1045   0.9222   0.0372
  -4.250  -0.0663   0.02305   0.01406  -0.1063   0.9190   0.0402
  -4.000  -0.0394   0.02209   0.01309  -0.1065   0.9117   0.0434
  -3.750  -0.0049   0.02117   0.01209  -0.1079   0.9071   0.0463
  -3.500   0.0333   0.02030   0.01106  -0.1100   0.9041   0.0508
  -3.250   0.0599   0.01961   0.01037  -0.1100   0.8956   0.0576
  -3.000   0.0972   0.01875   0.00957  -0.1120   0.8917   0.0827
  -2.750   0.1283   0.01797   0.00906  -0.1131   0.8851   0.1504
  -2.500   0.1621   0.01689   0.00872  -0.1151   0.8798   0.3153
  -2.250   0.1980   0.01622   0.00868  -0.1167   0.8762   0.5031
  -2.000   0.2237   0.01613   0.00864  -0.1160   0.8670   0.5662
  -1.750   0.2593   0.01593   0.00843  -0.1170   0.8624   0.6149
  -1.500   0.2854   0.01587   0.00833  -0.1163   0.8533   0.6486
  -1.250   0.3206   0.01568   0.00809  -0.1172   0.8482   0.6799
  -1.000   0.3462   0.01561   0.00800  -0.1164   0.8387   0.7053
  -0.750   0.3807   0.01539   0.00773  -0.1172   0.8332   0.7313
  -0.500   0.4061   0.01534   0.00765  -0.1164   0.8232   0.7551
  -0.250   0.4361   0.01516   0.00745  -0.1163   0.8158   0.7778
   0.000   0.4643   0.01502   0.00729  -0.1160   0.8070   0.8011
   0.250   0.4904   0.01489   0.00716  -0.1153   0.7976   0.8247
   0.500   0.5215   0.01467   0.00692  -0.1154   0.7903   0.8498
   0.750   0.5454   0.01456   0.00682  -0.1143   0.7796   0.8801
   1.000   0.5761   0.01438   0.00664  -0.1145   0.7703   0.9242
   1.250   0.6174   0.01422   0.00641  -0.1172   0.7617   1.0000
   1.500   0.6489   0.01432   0.00643  -0.1182   0.7506   1.0000
   1.750   0.6813   0.01441   0.00642  -0.1192   0.7402   1.0000
   2.000   0.7149   0.01447   0.00640  -0.1204   0.7305   1.0000
   2.250   0.7456   0.01460   0.00647  -0.1210   0.7195   1.0000
   2.500   0.7746   0.01475   0.00659  -0.1213   0.7080   1.0000
   2.750   0.8042   0.01491   0.00670  -0.1216   0.6968   1.0000
   3.000   0.8341   0.01507   0.00680  -0.1220   0.6859   1.0000
   3.250   0.8632   0.01524   0.00696  -0.1223   0.6746   1.0000
   3.500   0.8899   0.01545   0.00717  -0.1221   0.6623   1.0000
   3.750   0.9167   0.01567   0.00739  -0.1219   0.6500   1.0000
   4.000   0.9434   0.01589   0.00763  -0.1217   0.6374   1.0000
   4.250   0.9698   0.01611   0.00786  -0.1214   0.6245   1.0000
   4.500   0.9958   0.01635   0.00810  -0.1209   0.6111   1.0000
   4.750   1.0211   0.01660   0.00837  -0.1204   0.5972   1.0000
   5.000   1.0458   0.01686   0.00868  -0.1198   0.5827   1.0000
   5.250   1.0698   0.01713   0.00898  -0.1190   0.5673   1.0000
   5.500   1.0930   0.01741   0.00929  -0.1181   0.5509   1.0000
   5.750   1.1158   0.01770   0.00961  -0.1171   0.5336   1.0000
   6.000   1.1381   0.01802   0.00994  -0.1160   0.5157   1.0000
   6.250   1.1593   0.01836   0.01035  -0.1148   0.4968   1.0000
   6.500   1.1796   0.01874   0.01076  -0.1134   0.4764   1.0000
   6.750   1.1991   0.01915   0.01117  -0.1118   0.4549   1.0000
   7.000   1.2171   0.01960   0.01164  -0.1101   0.4308   1.0000
   7.250   1.2341   0.02012   0.01215  -0.1082   0.4054   1.0000
   7.500   1.2496   0.02070   0.01274  -0.1061   0.3782   1.0000
   7.750   1.2636   0.02136   0.01335  -0.1038   0.3494   1.0000
   8.000   1.2754   0.02211   0.01404  -0.1012   0.3189   1.0000
   8.250   1.2847   0.02296   0.01480  -0.0982   0.2882   1.0000
   8.500   1.2926   0.02394   0.01567  -0.0952   0.2575   1.0000
   8.750   1.2995   0.02504   0.01667  -0.0922   0.2277   1.0000
   9.000   1.3062   0.02622   0.01780  -0.0893   0.2005   1.0000
   9.250   1.3122   0.02751   0.01901  -0.0865   0.1752   1.0000
   9.500   1.3177   0.02888   0.02033  -0.0838   0.1538   1.0000
   9.750   1.3233   0.03031   0.02174  -0.0812   0.1346   1.0000
  10.000   1.3277   0.03187   0.02328  -0.0787   0.1185   1.0000
  10.250   1.3319   0.03352   0.02494  -0.0763   0.1049   1.0000
  10.500   1.3357   0.03526   0.02671  -0.0740   0.0926   1.0000
  10.750   1.3390   0.03710   0.02861  -0.0719   0.0819   1.0000
  11.000   1.3412   0.03912   0.03068  -0.0699   0.0728   1.0000
  11.250   1.3414   0.04138   0.03297  -0.0680   0.0645   1.0000
  11.500   1.3441   0.04353   0.03522  -0.0665   0.0558   1.0000
  11.750   1.3456   0.04587   0.03765  -0.0651   0.0481   1.0000
  12.000   1.3434   0.04865   0.04043  -0.0639   0.0424   1.0000
  12.250   1.3449   0.05121   0.04318  -0.0629   0.0370   1.0000
  12.500   1.3403   0.05450   0.04652  -0.0620   0.0335   1.0000
  12.750   1.3384   0.05766   0.04987  -0.0613   0.0303   1.0000
  13.000   1.3359   0.06100   0.05335  -0.0609   0.0274   1.0000
  13.250   1.3302   0.06481   0.05726  -0.0608   0.0254   1.0000
  13.500   1.3260   0.06863   0.06124  -0.0608   0.0235   1.0000
  13.750   1.3231   0.07242   0.06522  -0.0610   0.0217   1.0000
  14.000   1.3192   0.07645   0.06941  -0.0615   0.0203   1.0000
  14.250   1.3142   0.08074   0.07385  -0.0623   0.0194   1.0000
  14.500   1.3082   0.08530   0.07854  -0.0633   0.0187   1.0000
  14.750   1.3016   0.09004   0.08338  -0.0643   0.0181   1.0000
  15.000   1.2983   0.09448   0.08808  -0.0653   0.0175   1.0000
  15.250   1.2942   0.09918   0.09301  -0.0666   0.0170   1.0000
  15.500   1.2891   0.10417   0.09823  -0.0682   0.0166   1.0000
  15.750   1.2828   0.10951   0.10379  -0.0702   0.0162   1.0000
  16.000   1.2753   0.11520   0.10970  -0.0727   0.0159   1.0000
  16.250   1.2666   0.12132   0.11604  -0.0757   0.0157   1.0000
  16.500   1.2567   0.12790   0.12283  -0.0792   0.0155   1.0000
  16.750   1.2454   0.13503   0.13017  -0.0833   0.0154   1.0000
  17.000   1.2327   0.14286   0.13821  -0.0881   0.0153   1.0000
  17.250   1.2178   0.15159   0.14714  -0.0938   0.0154   1.0000
  17.500   1.2001   0.16168   0.15742  -0.1004   0.0156   1.0000
  17.750   1.1781   0.17398   0.16986  -0.1087   0.0160   1.0000
  18.000   1.1508   0.18956   0.18555  -0.1186   0.0165   1.0000
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