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E210 (13.64%) (e210-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: E210 (13.64%) (e210-il)
Reynolds number: 200,000
Max Cl/Cd: 78.69 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e210-il-200000.txt
Download as CSV file: xf-e210-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3676   0.09457   0.09145  -0.0404   1.0000   0.0655
  -8.500  -0.3999   0.09123   0.08825  -0.0420   1.0000   0.0665
  -8.250  -0.4292   0.08493   0.08203  -0.0500   0.9960   0.0668
  -8.000  -0.4208   0.07709   0.07422  -0.0562   0.9904   0.0682
  -7.750  -0.3877   0.07753   0.07463  -0.0513   0.9886   0.0700
  -7.500  -0.3661   0.07315   0.07024  -0.0575   0.9830   0.0725
  -7.250  -0.3958   0.04160   0.03718  -0.0919   0.9601   0.0463
  -7.000  -0.3730   0.03594   0.03106  -0.0942   0.9519   0.0411
  -6.750  -0.3402   0.03130   0.02580  -0.0978   0.9470   0.0408
  -6.500  -0.3106   0.02835   0.02238  -0.0993   0.9394   0.0415
  -6.250  -0.2745   0.02549   0.01906  -0.1015   0.9345   0.0417
  -6.000  -0.2335   0.02331   0.01653  -0.1043   0.9317   0.0426
  -5.750  -0.2037   0.02214   0.01510  -0.1046   0.9220   0.0443
  -5.500  -0.1646   0.02004   0.01292  -0.1070   0.9188   0.0470
  -5.250  -0.1333   0.01887   0.01172  -0.1076   0.9103   0.0493
  -5.000  -0.0936   0.01768   0.01047  -0.1097   0.9059   0.0527
  -4.750  -0.0573   0.01647   0.00925  -0.1114   0.8996   0.0583
  -4.500  -0.0190   0.01553   0.00827  -0.1134   0.8924   0.0665
  -4.250   0.0220   0.01411   0.00701  -0.1163   0.8862   0.0979
  -4.000   0.0595   0.01293   0.00621  -0.1187   0.8765   0.1847
  -3.750   0.0965   0.01206   0.00569  -0.1209   0.8654   0.2798
  -3.500   0.1344   0.01143   0.00545  -0.1232   0.8539   0.4021
  -3.250   0.1712   0.01132   0.00536  -0.1247   0.8407   0.4754
  -3.000   0.2051   0.01130   0.00527  -0.1255   0.8261   0.5120
  -2.750   0.2367   0.01133   0.00517  -0.1259   0.8110   0.5374
  -2.500   0.2666   0.01137   0.00511  -0.1260   0.7960   0.5589
  -2.250   0.2954   0.01145   0.00508  -0.1259   0.7817   0.5790
  -2.000   0.3233   0.01152   0.00506  -0.1256   0.7678   0.5973
  -1.750   0.3501   0.01159   0.00504  -0.1252   0.7542   0.6131
  -1.500   0.3768   0.01166   0.00503  -0.1248   0.7415   0.6280
  -1.250   0.4038   0.01173   0.00503  -0.1244   0.7299   0.6420
  -1.000   0.4314   0.01181   0.00500  -0.1242   0.7194   0.6560
  -0.750   0.4578   0.01187   0.00502  -0.1238   0.7085   0.6699
  -0.500   0.4842   0.01195   0.00505  -0.1234   0.6984   0.6837
  -0.250   0.5121   0.01204   0.00504  -0.1233   0.6896   0.6976
   0.000   0.5376   0.01209   0.00510  -0.1227   0.6798   0.7109
   0.250   0.5642   0.01217   0.00515  -0.1224   0.6715   0.7248
   0.500   0.5903   0.01223   0.00520  -0.1219   0.6629   0.7395
   0.750   0.6163   0.01230   0.00528  -0.1215   0.6548   0.7549
   1.000   0.6423   0.01236   0.00534  -0.1210   0.6470   0.7714
   1.250   0.6678   0.01244   0.00544  -0.1205   0.6396   0.7901
   1.500   0.6922   0.01248   0.00552  -0.1196   0.6321   0.8100
   1.750   0.7159   0.01255   0.00562  -0.1186   0.6253   0.8350
   2.000   0.7372   0.01255   0.00571  -0.1170   0.6181   0.8662
   2.250   0.7594   0.01255   0.00574  -0.1155   0.6121   0.9104
   2.500   0.7978   0.01253   0.00577  -0.1178   0.6041   1.0000
   2.750   0.8300   0.01278   0.00588  -0.1191   0.5981   1.0000
   3.000   0.8569   0.01298   0.00609  -0.1193   0.5906   1.0000
   3.250   0.8860   0.01320   0.00622  -0.1197   0.5843   1.0000
   3.500   0.9128   0.01344   0.00647  -0.1197   0.5777   1.0000
   3.750   0.9402   0.01366   0.00665  -0.1198   0.5710   1.0000
   4.000   0.9682   0.01393   0.00687  -0.1199   0.5651   1.0000
   4.250   0.9937   0.01415   0.00714  -0.1196   0.5581   1.0000
   4.500   1.0226   0.01441   0.00732  -0.1199   0.5523   1.0000
   4.750   1.0468   0.01465   0.00764  -0.1194   0.5451   1.0000
   5.000   1.0741   0.01487   0.00784  -0.1193   0.5386   1.0000
   5.250   1.0991   0.01513   0.00814  -0.1189   0.5316   1.0000
   5.500   1.1250   0.01533   0.00835  -0.1186   0.5243   1.0000
   5.750   1.1501   0.01557   0.00862  -0.1181   0.5170   1.0000
   6.000   1.1750   0.01576   0.00884  -0.1176   0.5091   1.0000
   6.250   1.1995   0.01599   0.00911  -0.1171   0.5016   1.0000
   6.500   1.2239   0.01617   0.00932  -0.1165   0.4935   1.0000
   6.750   1.2473   0.01639   0.00962  -0.1157   0.4854   1.0000
   7.000   1.2715   0.01656   0.00979  -0.1150   0.4769   1.0000
   7.250   1.2928   0.01676   0.01009  -0.1139   0.4677   1.0000
   7.500   1.3169   0.01695   0.01026  -0.1132   0.4591   1.0000
   7.750   1.3364   0.01712   0.01056  -0.1117   0.4488   1.0000
   8.000   1.3568   0.01733   0.01084  -0.1103   0.4388   1.0000
   8.250   1.3777   0.01753   0.01105  -0.1091   0.4285   1.0000
   8.500   1.3952   0.01773   0.01134  -0.1072   0.4167   1.0000
   8.750   1.4120   0.01797   0.01168  -0.1052   0.4043   1.0000
   9.000   1.4277   0.01823   0.01201  -0.1031   0.3908   1.0000
   9.250   1.4417   0.01853   0.01236  -0.1007   0.3761   1.0000
   9.500   1.4529   0.01888   0.01275  -0.0978   0.3605   1.0000
   9.750   1.4615   0.01931   0.01320  -0.0945   0.3435   1.0000
  10.000   1.4683   0.01988   0.01375  -0.0910   0.3252   1.0000
  10.250   1.4741   0.02055   0.01445  -0.0875   0.3029   1.0000
  10.500   1.4765   0.02145   0.01529  -0.0838   0.2794   1.0000
  10.750   1.4761   0.02260   0.01635  -0.0799   0.2536   1.0000
  11.000   1.4738   0.02399   0.01766  -0.0761   0.2278   1.0000
  11.250   1.4693   0.02565   0.01922  -0.0724   0.2043   1.0000
  11.500   1.4632   0.02759   0.02107  -0.0690   0.1830   1.0000
  11.750   1.4573   0.02972   0.02313  -0.0660   0.1642   1.0000
  12.000   1.4516   0.03202   0.02539  -0.0634   0.1467   1.0000
  12.250   1.4456   0.03455   0.02788  -0.0613   0.1316   1.0000
  12.500   1.4397   0.03726   0.03057  -0.0595   0.1184   1.0000
  12.750   1.4340   0.04013   0.03345  -0.0581   0.1068   1.0000
  13.000   1.4274   0.04326   0.03657  -0.0570   0.0973   1.0000
  13.250   1.4217   0.04647   0.03979  -0.0562   0.0882   1.0000
  13.500   1.4185   0.04956   0.04294  -0.0556   0.0800   1.0000
  13.750   1.4101   0.05331   0.04668  -0.0553   0.0738   1.0000
  14.000   1.4079   0.05654   0.05000  -0.0551   0.0669   1.0000
  14.250   1.4005   0.06043   0.05392  -0.0551   0.0615   1.0000
  14.500   1.3973   0.06398   0.05755  -0.0553   0.0558   1.0000
  14.750   1.3888   0.06826   0.06184  -0.0556   0.0513   1.0000
  15.000   1.3860   0.07196   0.06566  -0.0561   0.0461   1.0000
  15.250   1.3760   0.07664   0.07032  -0.0568   0.0423   1.0000
  15.500   1.3733   0.08055   0.07437  -0.0574   0.0381   1.0000
  15.750   1.3648   0.08524   0.07906  -0.0584   0.0350   1.0000
  16.000   1.3609   0.08936   0.08330  -0.0591   0.0319   1.0000
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