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EPPLER 855 AIRFOIL (e855-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 855 AIRFOIL (e855-il)
Reynolds number: 200,000
Max Cl/Cd: 76.37 at α=9.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e855-il-200000.txt
Download as CSV file: xf-e855-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 855 AIRFOIL                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.4196   0.08563   0.08230  -0.0605   1.0000   0.0306
 -10.500  -0.4306   0.08118   0.07791  -0.0611   1.0000   0.0297
 -10.250  -0.4586   0.07411   0.07085  -0.0641   1.0000   0.0289
 -10.000  -0.4882   0.06860   0.06533  -0.0659   1.0000   0.0283
  -9.750  -0.5227   0.06443   0.06116  -0.0660   1.0000   0.0282
  -9.500  -0.6099   0.05251   0.04841  -0.0764   0.9885   0.0247
  -9.250  -0.5907   0.04749   0.04310  -0.0813   0.9814   0.0240
  -9.000  -0.5749   0.04184   0.03699  -0.0858   0.9731   0.0236
  -8.750  -0.5568   0.03748   0.03220  -0.0883   0.9640   0.0233
  -8.500  -0.5325   0.03362   0.02782  -0.0906   0.9569   0.0235
  -8.250  -0.5036   0.03066   0.02441  -0.0926   0.9501   0.0240
  -8.000  -0.4757   0.02788   0.02131  -0.0939   0.9432   0.0250
  -7.750  -0.4422   0.02631   0.01973  -0.0960   0.9372   0.0271
  -7.500  -0.4028   0.02473   0.01794  -0.0988   0.9341   0.0299
  -7.250  -0.3771   0.02274   0.01583  -0.0987   0.9245   0.0323
  -7.000  -0.3392   0.02125   0.01434  -0.1012   0.9209   0.0366
  -6.750  -0.3105   0.01988   0.01297  -0.1019   0.9121   0.0435
  -6.500  -0.2724   0.01849   0.01156  -0.1044   0.9074   0.0546
  -6.250  -0.2374   0.01740   0.01045  -0.1063   0.8996   0.0693
  -6.000  -0.1972   0.01614   0.00924  -0.1094   0.8933   0.0905
  -5.750  -0.1590   0.01501   0.00821  -0.1122   0.8848   0.1220
  -5.500  -0.1189   0.01362   0.00712  -0.1157   0.8766   0.1910
  -5.250  -0.0870   0.01243   0.00657  -0.1177   0.8643   0.3388
  -5.000  -0.0505   0.01234   0.00652  -0.1193   0.8523   0.4083
  -4.750  -0.0142   0.01243   0.00646  -0.1208   0.8402   0.4416
  -4.500   0.0201   0.01256   0.00643  -0.1218   0.8278   0.4645
  -4.250   0.0514   0.01272   0.00646  -0.1222   0.8149   0.4824
  -4.000   0.0796   0.01287   0.00648  -0.1221   0.8015   0.4975
  -3.750   0.1076   0.01300   0.00647  -0.1219   0.7890   0.5107
  -3.500   0.1359   0.01311   0.00646  -0.1218   0.7773   0.5222
  -3.250   0.1646   0.01320   0.00646  -0.1218   0.7666   0.5322
  -3.000   0.1914   0.01329   0.00643  -0.1214   0.7554   0.5434
  -2.750   0.2180   0.01344   0.00647  -0.1210   0.7449   0.5558
  -2.500   0.2457   0.01353   0.00652  -0.1208   0.7359   0.5652
  -2.250   0.2721   0.01356   0.00645  -0.1205   0.7259   0.5740
  -2.000   0.2990   0.01360   0.00643  -0.1202   0.7169   0.5809
  -1.750   0.3273   0.01362   0.00629  -0.1204   0.7088   0.5883
  -1.500   0.3535   0.01363   0.00630  -0.1200   0.7003   0.5937
  -1.250   0.3821   0.01367   0.00620  -0.1202   0.6929   0.6007
  -1.000   0.4081   0.01368   0.00619  -0.1199   0.6848   0.6065
  -0.750   0.4363   0.01372   0.00615  -0.1200   0.6780   0.6126
  -0.500   0.4631   0.01377   0.00615  -0.1200   0.6710   0.6196
  -0.250   0.4903   0.01380   0.00616  -0.1199   0.6644   0.6253
   0.000   0.5182   0.01389   0.00617  -0.1200   0.6582   0.6324
   0.250   0.5444   0.01392   0.00622  -0.1197   0.6513   0.6386
   0.500   0.5735   0.01401   0.00623  -0.1201   0.6462   0.6459
   0.750   0.5989   0.01408   0.00634  -0.1197   0.6399   0.6527
   1.000   0.6262   0.01415   0.00641  -0.1197   0.6342   0.6603
   1.250   0.6549   0.01427   0.00647  -0.1199   0.6293   0.6681
   1.500   0.6796   0.01435   0.00663  -0.1194   0.6232   0.6761
   1.750   0.7074   0.01444   0.00672  -0.1195   0.6183   0.6847
   2.000   0.7358   0.01459   0.00685  -0.1198   0.6139   0.6945
   2.250   0.7598   0.01467   0.00705  -0.1191   0.6081   0.7034
   2.500   0.7872   0.01478   0.00716  -0.1191   0.6032   0.7143
   2.750   0.8163   0.01494   0.00732  -0.1195   0.5993   0.7263
   3.000   0.8390   0.01505   0.00759  -0.1186   0.5940   0.7382
   3.250   0.8648   0.01516   0.00777  -0.1183   0.5891   0.7518
   3.500   0.8931   0.01529   0.00793  -0.1184   0.5852   0.7676
   3.750   0.9159   0.01544   0.00823  -0.1175   0.5804   0.7858
   4.000   0.9389   0.01555   0.00848  -0.1166   0.5756   0.8067
   4.250   0.9637   0.01562   0.00864  -0.1159   0.5715   0.8327
   4.500   0.9862   0.01572   0.00886  -0.1147   0.5676   0.8687
   4.750   1.0099   0.01572   0.00911  -0.1138   0.5624   0.9424
   5.000   1.0459   0.01592   0.00931  -0.1160   0.5576   1.0000
   5.250   1.0789   0.01621   0.00951  -0.1173   0.5537   1.0000
   5.500   1.0999   0.01649   0.00992  -0.1163   0.5478   1.0000
   5.750   1.1268   0.01669   0.01013  -0.1164   0.5423   1.0000
   6.000   1.1558   0.01693   0.01033  -0.1168   0.5372   1.0000
   6.250   1.1765   0.01715   0.01067  -0.1156   0.5304   1.0000
   6.500   1.2061   0.01723   0.01070  -0.1159   0.5241   1.0000
   6.750   1.2248   0.01739   0.01098  -0.1143   0.5159   1.0000
   7.000   1.2532   0.01744   0.01096  -0.1144   0.5088   1.0000
   7.250   1.2712   0.01763   0.01130  -0.1127   0.5010   1.0000
   7.500   1.2980   0.01771   0.01136  -0.1125   0.4940   1.0000
   7.750   1.3157   0.01790   0.01169  -0.1107   0.4860   1.0000
   8.000   1.3412   0.01797   0.01174  -0.1103   0.4784   1.0000
   8.250   1.3568   0.01814   0.01207  -0.1080   0.4695   1.0000
   8.500   1.3786   0.01823   0.01219  -0.1069   0.4610   1.0000
   8.750   1.3934   0.01835   0.01242  -0.1045   0.4509   1.0000
   9.000   1.4077   0.01848   0.01266  -0.1020   0.4401   1.0000
   9.250   1.4212   0.01861   0.01284  -0.0994   0.4286   1.0000
   9.500   1.4313   0.01876   0.01303  -0.0962   0.4160   1.0000
   9.750   1.4377   0.01900   0.01332  -0.0923   0.4022   1.0000
  10.000   1.4429   0.01935   0.01376  -0.0884   0.3863   1.0000
  10.250   1.4465   0.01982   0.01429  -0.0844   0.3672   1.0000
  10.500   1.4475   0.02050   0.01493  -0.0802   0.3449   1.0000
  10.750   1.4447   0.02145   0.01583  -0.0758   0.3168   1.0000
  11.000   1.4368   0.02283   0.01707  -0.0711   0.2861   1.0000
  11.250   1.4245   0.02468   0.01876  -0.0665   0.2551   1.0000
  11.750   1.3978   0.02946   0.02328  -0.0589   0.2027   1.0000
  12.000   1.3851   0.03225   0.02598  -0.0560   0.1818   1.0000
  12.250   1.3742   0.03516   0.02882  -0.0538   0.1630   1.0000
  12.500   1.3641   0.03824   0.03185  -0.0520   0.1474   1.0000
  12.750   1.3549   0.04142   0.03499  -0.0506   0.1336   1.0000
  13.000   1.3473   0.04462   0.03817  -0.0495   0.1217   1.0000
  13.250   1.3397   0.04793   0.04148  -0.0486   0.1113   1.0000
  13.500   1.3308   0.05152   0.04503  -0.0479   0.1023   1.0000
  13.750   1.3281   0.05460   0.04817  -0.0475   0.0929   1.0000
  14.000   1.3231   0.05799   0.05157  -0.0471   0.0852   1.0000
  14.250   1.3176   0.06154   0.05510  -0.0470   0.0783   1.0000
  14.500   1.3162   0.06472   0.05836  -0.0469   0.0714   1.0000
  14.750   1.3109   0.06840   0.06200  -0.0470   0.0659   1.0000
  15.000   1.3110   0.07154   0.06525  -0.0472   0.0602   1.0000
  15.250   1.3075   0.07519   0.06889  -0.0475   0.0554   1.0000
  15.500   1.3067   0.07853   0.07231  -0.0478   0.0508   1.0000
  15.750   1.3055   0.08206   0.07590  -0.0484   0.0465   1.0000
  16.000   1.3026   0.08569   0.07954  -0.0488   0.0427   1.0000
  16.250   1.3030   0.08916   0.08313  -0.0495   0.0391   1.0000
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