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E210 (13.64%) (e210-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: E210 (13.64%) (e210-il)
Reynolds number: 100,000
Max Cl/Cd: 52.66 at α=10.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e210-il-100000.txt
Download as CSV file: xf-e210-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E210  (13.64%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3797   0.09718   0.09301  -0.0348   1.0000   0.1366
  -7.750  -0.4230   0.09667   0.09270  -0.0329   1.0000   0.1373
  -7.500  -0.4620   0.09490   0.09109  -0.0337   1.0000   0.1376
  -7.250  -0.4085   0.09101   0.08712  -0.0266   1.0000   0.1423
  -7.000  -0.4250   0.08999   0.08620  -0.0232   1.0000   0.1443
  -6.750  -0.4392   0.08786   0.08416  -0.0243   0.9972   0.1488
  -6.500  -0.4190   0.08144   0.07773  -0.0350   0.9867   0.1570
  -6.250  -0.4189   0.05007   0.04494  -0.0736   0.9697   0.0824
  -6.000  -0.3867   0.04337   0.03764  -0.0786   0.9614   0.0732
  -5.750  -0.3515   0.03833   0.03185  -0.0829   0.9532   0.0719
  -5.500  -0.3098   0.03475   0.02765  -0.0869   0.9467   0.0728
  -5.250  -0.2736   0.03192   0.02428  -0.0891   0.9376   0.0732
  -5.000  -0.2281   0.02966   0.02156  -0.0925   0.9322   0.0762
  -4.750  -0.1931   0.02805   0.01959  -0.0939   0.9220   0.0812
  -4.500  -0.1499   0.02626   0.01782  -0.0967   0.9163   0.0874
  -4.250  -0.1147   0.02487   0.01634  -0.0979   0.9067   0.0964
  -4.000  -0.0780   0.02359   0.01521  -0.0996   0.8982   0.1158
  -3.750  -0.0373   0.02179   0.01380  -0.1022   0.8914   0.1787
  -3.500  -0.0024   0.02019   0.01302  -0.1044   0.8827   0.3182
  -3.250   0.0384   0.01976   0.01309  -0.1063   0.8760   0.4779
  -3.000   0.0709   0.01979   0.01312  -0.1063   0.8662   0.5361
  -2.750   0.1139   0.01959   0.01287  -0.1080   0.8608   0.5821
  -2.500   0.1454   0.01955   0.01278  -0.1078   0.8509   0.6158
  -2.250   0.1871   0.01925   0.01241  -0.1093   0.8453   0.6484
  -2.000   0.2153   0.01916   0.01229  -0.1085   0.8347   0.6722
  -1.750   0.2576   0.01877   0.01180  -0.1102   0.8292   0.6983
  -1.500   0.2826   0.01871   0.01172  -0.1091   0.8177   0.7178
  -1.250   0.3146   0.01852   0.01145  -0.1091   0.8090   0.7383
  -1.000   0.3473   0.01832   0.01115  -0.1095   0.8002   0.7590
  -0.750   0.3715   0.01829   0.01108  -0.1083   0.7896   0.7765
  -0.500   0.4065   0.01801   0.01071  -0.1089   0.7827   0.7947
  -0.250   0.4259   0.01807   0.01076  -0.1070   0.7713   0.8122
   0.000   0.4502   0.01804   0.01069  -0.1060   0.7621   0.8312
   0.250   0.4786   0.01793   0.01050  -0.1057   0.7538   0.8521
   0.500   0.4969   0.01798   0.01056  -0.1036   0.7439   0.8732
   0.750   0.5279   0.01779   0.01029  -0.1037   0.7370   0.8985
   1.000   0.5514   0.01786   0.01041  -0.1029   0.7268   0.9295
   1.250   0.6057   0.01776   0.01021  -0.1081   0.7194   0.9624
   1.500   0.6543   0.01788   0.01027  -0.1134   0.7096   1.0000
   1.750   0.6816   0.01819   0.01046  -0.1147   0.7013   1.0000
   2.000   0.7134   0.01846   0.01060  -0.1162   0.6932   1.0000
   2.250   0.7406   0.01888   0.01095  -0.1167   0.6849   1.0000
   2.500   0.7716   0.01916   0.01112  -0.1176   0.6774   1.0000
   2.750   0.7963   0.01964   0.01157  -0.1175   0.6693   1.0000
   3.000   0.8261   0.01994   0.01181  -0.1180   0.6621   1.0000
   3.250   0.8500   0.02046   0.01232  -0.1176   0.6542   1.0000
   3.500   0.8783   0.02080   0.01262  -0.1179   0.6470   1.0000
   3.750   0.9026   0.02132   0.01316  -0.1175   0.6396   1.0000
   4.000   0.9290   0.02173   0.01356  -0.1174   0.6322   1.0000
   4.250   0.9545   0.02223   0.01406  -0.1172   0.6252   1.0000
   4.500   0.9786   0.02271   0.01459  -0.1167   0.6174   1.0000
   4.750   1.0062   0.02314   0.01502  -0.1168   0.6110   1.0000
   5.000   1.0273   0.02373   0.01569  -0.1158   0.6027   1.0000
   5.250   1.0577   0.02405   0.01599  -0.1162   0.5965   1.0000
   5.500   1.0757   0.02475   0.01681  -0.1148   0.5877   1.0000
   5.750   1.1073   0.02498   0.01702  -0.1153   0.5813   1.0000
   6.000   1.1242   0.02568   0.01785  -0.1138   0.5721   1.0000
   6.250   1.1531   0.02594   0.01815  -0.1138   0.5648   1.0000
   6.500   1.1740   0.02643   0.01874  -0.1127   0.5556   1.0000
   6.750   1.1976   0.02685   0.01923  -0.1119   0.5471   1.0000
   7.000   1.2259   0.02696   0.01938  -0.1118   0.5385   1.0000
   7.250   1.2438   0.02753   0.02009  -0.1102   0.5287   1.0000
   7.500   1.2799   0.02729   0.01981  -0.1110   0.5204   1.0000
   7.750   1.2952   0.02776   0.02046  -0.1089   0.5093   1.0000
   8.000   1.3160   0.02803   0.02084  -0.1076   0.4987   1.0000
   8.250   1.3466   0.02779   0.02061  -0.1075   0.4884   1.0000
   8.500   1.3702   0.02774   0.02063  -0.1065   0.4766   1.0000
   8.750   1.3869   0.02793   0.02096  -0.1044   0.4640   1.0000
   9.000   1.4060   0.02795   0.02110  -0.1026   0.4511   1.0000
   9.250   1.4253   0.02789   0.02113  -0.1008   0.4375   1.0000
   9.500   1.4428   0.02784   0.02115  -0.0987   0.4230   1.0000
   9.750   1.4571   0.02783   0.02123  -0.0962   0.4075   1.0000
  10.000   1.4683   0.02790   0.02136  -0.0931   0.3909   1.0000
  10.250   1.4766   0.02804   0.02157  -0.0897   0.3733   1.0000
  10.500   1.4810   0.02827   0.02180  -0.0857   0.3551   1.0000
  10.750   1.4762   0.02897   0.02258  -0.0806   0.3358   1.0000
  11.000   1.4718   0.02982   0.02345  -0.0759   0.3147   1.0000
  11.250   1.4659   0.03098   0.02457  -0.0715   0.2925   1.0000
  11.500   1.4574   0.03255   0.02607  -0.0673   0.2697   1.0000
  11.750   1.4476   0.03452   0.02795  -0.0636   0.2472   1.0000
  12.000   1.4371   0.03685   0.03016  -0.0603   0.2264   1.0000
  12.250   1.4269   0.03949   0.03266  -0.0576   0.2071   1.0000
  12.500   1.4171   0.04236   0.03547  -0.0553   0.1889   1.0000
  12.750   1.4087   0.04535   0.03839  -0.0535   0.1728   1.0000
  13.000   1.4016   0.04842   0.04138  -0.0520   0.1581   1.0000
  13.250   1.3957   0.05153   0.04446  -0.0509   0.1446   1.0000
  13.500   1.3912   0.05464   0.04753  -0.0499   0.1323   1.0000
  13.750   1.3876   0.05778   0.05063  -0.0491   0.1212   1.0000
  14.000   1.3854   0.06084   0.05361  -0.0484   0.1107   1.0000
  14.250   1.3806   0.06428   0.05711  -0.0482   0.1017   1.0000
  14.500   1.3771   0.06775   0.06067  -0.0479   0.0931   1.0000
  14.750   1.3763   0.07092   0.06377  -0.0477   0.0848   1.0000
  15.000   1.3711   0.07472   0.06770  -0.0480   0.0780   1.0000
  15.250   1.3698   0.07822   0.07124  -0.0479   0.0712   1.0000
  15.500   1.3678   0.08174   0.07479  -0.0482   0.0654   1.0000
  15.750   1.3671   0.08545   0.07862  -0.0483   0.0599   1.0000
  16.000   1.3650   0.08921   0.08250  -0.0488   0.0556   1.0000
  16.250   1.3720   0.09211   0.08541  -0.0484   0.0512   1.0000
  16.500   1.3644   0.09687   0.09047  -0.0496   0.0488   1.0000
  16.750   1.3590   0.10131   0.09509  -0.0508   0.0464   1.0000
  17.000   1.3741   0.10322   0.09681  -0.0500   0.0427   1.0000
  17.250   1.3609   0.10890   0.10283  -0.0521   0.0421   1.0000
  17.500   1.3468   0.11500   0.10924  -0.0547   0.0416   1.0000
  17.750   1.3315   0.12150   0.11603  -0.0577   0.0412   1.0000
  18.000   1.3142   0.12858   0.12338  -0.0614   0.0410   1.0000
  18.250   1.2942   0.13642   0.13148  -0.0660   0.0410   1.0000
  18.500   1.2724   0.14500   0.14030  -0.0713   0.0412   1.0000
  18.750   1.2489   0.15443   0.14994  -0.0775   0.0416   1.0000
  19.000   1.2240   0.16482   0.16049  -0.0845   0.0421   1.0000
  19.250   1.1997   0.17585   0.17161  -0.0919   0.0426   1.0000
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