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EPPLER 550 AIRFOIL (e550-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 550 AIRFOIL (e550-il)
Reynolds number: 100,000
Max Cl/Cd: 40.81 at α=9.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e550-il-100000-n5.txt
Download as CSV file: xf-e550-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 550 AIRFOIL                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.5322   0.09377   0.08831  -0.0548   1.0000   0.0185
 -13.500  -0.5521   0.08661   0.08105  -0.0589   1.0000   0.0183
 -13.250  -0.5738   0.08009   0.07439  -0.0623   1.0000   0.0182
 -13.000  -0.5947   0.07438   0.06852  -0.0648   1.0000   0.0182
 -12.750  -0.6128   0.06950   0.06348  -0.0665   1.0000   0.0181
 -12.500  -0.6277   0.06529   0.05911  -0.0674   1.0000   0.0180
 -12.250  -0.6449   0.06107   0.05467  -0.0679   1.0000   0.0181
 -12.000  -0.6574   0.05749   0.05090  -0.0677   1.0000   0.0181
 -11.750  -0.6679   0.05424   0.04743  -0.0671   1.0000   0.0181
 -11.500  -0.6768   0.05114   0.04408  -0.0660   1.0000   0.0182
 -11.250  -0.6817   0.04846   0.04116  -0.0646   1.0000   0.0184
 -11.000  -0.6825   0.04612   0.03858  -0.0631   1.0000   0.0185
 -10.750  -0.6794   0.04403   0.03636  -0.0615   1.0000   0.0187
 -10.500  -0.6740   0.04232   0.03460  -0.0599   1.0000   0.0191
 -10.250  -0.6693   0.04089   0.03312  -0.0582   1.0000   0.0196
 -10.000  -0.6637   0.03949   0.03165  -0.0562   1.0000   0.0203
  -9.750  -0.6571   0.03818   0.03026  -0.0541   1.0000   0.0209
  -9.500  -0.6323   0.03634   0.02819  -0.0547   0.9854   0.0226
  -9.250  -0.5999   0.03469   0.02652  -0.0571   0.9575   0.0241
  -9.000  -0.5579   0.03302   0.02470  -0.0600   0.9355   0.0258
  -8.750  -0.5149   0.03133   0.02292  -0.0637   0.9122   0.0282
  -8.500  -0.4731   0.02990   0.02129  -0.0675   0.8858   0.0321
  -8.250  -0.4399   0.02854   0.01984  -0.0702   0.8584   0.0368
  -8.000  -0.4169   0.02738   0.01857  -0.0709   0.8323   0.0417
  -7.750  -0.3997   0.02635   0.01745  -0.0704   0.8101   0.0489
  -7.500  -0.3873   0.02541   0.01644  -0.0691   0.7904   0.0580
  -7.250  -0.3781   0.02453   0.01553  -0.0672   0.7734   0.0698
  -7.000  -0.3706   0.02365   0.01468  -0.0651   0.7587   0.0882
  -6.750  -0.3629   0.02269   0.01385  -0.0631   0.7456   0.1170
  -6.500  -0.3579   0.02156   0.01295  -0.0609   0.7337   0.1631
  -6.250  -0.3567   0.02010   0.01189  -0.0585   0.7234   0.2396
  -6.000  -0.3575   0.01868   0.01135  -0.0552   0.7134   0.3818
  -5.750  -0.3329   0.01968   0.01274  -0.0529   0.7038   0.5017
  -5.500  -0.3109   0.01983   0.01261  -0.0522   0.6949   0.5379
  -5.250  -0.2846   0.02056   0.01317  -0.0510   0.6859   0.5595
  -5.000  -0.2578   0.02119   0.01360  -0.0500   0.6783   0.5758
  -4.750  -0.2316   0.02176   0.01402  -0.0489   0.6707   0.5897
  -4.500  -0.2045   0.02264   0.01476  -0.0474   0.6636   0.6051
  -4.250  -0.1787   0.02331   0.01527  -0.0461   0.6572   0.6194
  -4.000  -0.1498   0.02387   0.01575  -0.0450   0.6500   0.6247
  -3.750  -0.1250   0.02370   0.01536  -0.0448   0.6444   0.6300
  -3.500  -0.1028   0.02325   0.01474  -0.0448   0.6381   0.6360
  -3.250  -0.0763   0.02321   0.01458  -0.0445   0.6323   0.6384
  -3.000  -0.0498   0.02312   0.01432  -0.0444   0.6278   0.6412
  -2.750  -0.0247   0.02293   0.01402  -0.0443   0.6225   0.6445
  -2.500  -0.0001   0.02262   0.01357  -0.0445   0.6171   0.6487
  -2.250   0.0255   0.02229   0.01305  -0.0450   0.6126   0.6524
  -2.000   0.0520   0.02222   0.01288  -0.0449   0.6081   0.6542
  -1.750   0.0777   0.02215   0.01276  -0.0447   0.6030   0.6564
  -1.500   0.1040   0.02206   0.01257  -0.0448   0.5988   0.6587
  -1.250   0.1311   0.02193   0.01231  -0.0451   0.5953   0.6611
  -1.000   0.1576   0.02180   0.01209  -0.0454   0.5915   0.6641
  -0.750   0.1837   0.02164   0.01185  -0.0459   0.5869   0.6676
  -0.500   0.2103   0.02156   0.01171  -0.0461   0.5828   0.6696
  -0.250   0.2376   0.02154   0.01161  -0.0462   0.5794   0.6711
   0.000   0.2649   0.02154   0.01154  -0.0464   0.5763   0.6729
   0.250   0.2902   0.02159   0.01161  -0.0463   0.5723   0.6752
   0.500   0.3165   0.02161   0.01162  -0.0465   0.5686   0.6778
   0.750   0.3438   0.02160   0.01156  -0.0468   0.5652   0.6804
   1.000   0.3723   0.02157   0.01143  -0.0475   0.5622   0.6830
   1.250   0.3996   0.02160   0.01143  -0.0480   0.5589   0.6854
   1.500   0.4244   0.02174   0.01163  -0.0477   0.5552   0.6871
   1.750   0.4500   0.02186   0.01179  -0.0476   0.5518   0.6892
   2.000   0.4767   0.02195   0.01189  -0.0477   0.5486   0.6915
   2.250   0.5047   0.02203   0.01193  -0.0480   0.5458   0.6941
   2.500   0.5316   0.02216   0.01206  -0.0483   0.5429   0.6967
   2.750   0.5562   0.02237   0.01234  -0.0484   0.5391   0.6995
   3.000   0.5823   0.02253   0.01255  -0.0486   0.5355   0.7021
   3.250   0.6084   0.02267   0.01273  -0.0486   0.5323   0.7040
   3.500   0.6357   0.02280   0.01287  -0.0487   0.5297   0.7064
   3.750   0.6621   0.02300   0.01312  -0.0488   0.5269   0.7092
   4.000   0.6839   0.02334   0.01360  -0.0483   0.5226   0.7124
   4.250   0.7090   0.02358   0.01391  -0.0484   0.5188   0.7157
   4.500   0.7361   0.02375   0.01412  -0.0487   0.5156   0.7186
   4.750   0.7638   0.02387   0.01427  -0.0488   0.5129   0.7210
   5.000   0.7858   0.02421   0.01475  -0.0482   0.5090   0.7237
   5.250   0.8066   0.02460   0.01529  -0.0476   0.5043   0.7269
   5.500   0.8321   0.02481   0.01557  -0.0476   0.5004   0.7305
   5.750   0.8612   0.02491   0.01569  -0.0481   0.4972   0.7346
   6.000   0.8829   0.02522   0.01615  -0.0474   0.4930   0.7378
   6.250   0.9009   0.02567   0.01679  -0.0463   0.4876   0.7415
   6.500   0.9264   0.02582   0.01701  -0.0461   0.4834   0.7456
   6.750   0.9574   0.02579   0.01701  -0.0468   0.4800   0.7499
   7.000   0.9702   0.02641   0.01786  -0.0450   0.4738   0.7536
   7.250   0.9920   0.02663   0.01821  -0.0443   0.4685   0.7577
   7.500   1.0224   0.02651   0.01814  -0.0447   0.4644   0.7626
   7.750   1.0352   0.02712   0.01896  -0.0430   0.4576   0.7680
   8.000   1.0560   0.02724   0.01922  -0.0420   0.4517   0.7730
   8.250   1.0860   0.02704   0.01907  -0.0423   0.4469   0.7791
   8.500   1.0916   0.02776   0.02005  -0.0396   0.4387   0.7855
   8.750   1.1187   0.02752   0.01989  -0.0393   0.4330   0.7918
   9.250   1.1455   0.02807   0.02079  -0.0355   0.4179   0.8069
   9.500   1.1467   0.02873   0.02166  -0.0322   0.4095   0.8166
   9.750   1.1623   0.02866   0.02170  -0.0302   0.4019   0.8269
  10.000   1.1537   0.02974   0.02301  -0.0259   0.3928   0.8411
  10.250   1.1670   0.02978   0.02317  -0.0239   0.3844   0.8584
  10.500   1.1533   0.03128   0.02493  -0.0199   0.3741   0.8889
  10.750   1.1482   0.03269   0.02653  -0.0179   0.3632   1.0000
  11.000   1.1525   0.03411   0.02799  -0.0171   0.3512   1.0000
  11.250   1.1565   0.03565   0.02955  -0.0164   0.3383   1.0000
  11.500   1.1588   0.03742   0.03132  -0.0157   0.3245   1.0000
  11.750   1.1605   0.03933   0.03322  -0.0151   0.3101   1.0000
  12.000   1.1599   0.04154   0.03540  -0.0146   0.2947   1.0000
  12.250   1.1599   0.04377   0.03761  -0.0141   0.2795   1.0000
  12.500   1.1589   0.04615   0.03995  -0.0138   0.2642   1.0000
  12.750   1.1577   0.04863   0.04238  -0.0134   0.2494   1.0000
  13.000   1.1556   0.05126   0.04497  -0.0132   0.2352   1.0000
  13.250   1.1522   0.05415   0.04783  -0.0132   0.2212   1.0000
  13.500   1.1491   0.05712   0.05079  -0.0133   0.2080   1.0000
  13.750   1.1465   0.06013   0.05379  -0.0135   0.1952   1.0000
  14.000   1.1443   0.06318   0.05684  -0.0138   0.1831   1.0000
  14.250   1.1426   0.06626   0.05991  -0.0142   0.1718   1.0000
  14.500   1.1406   0.06942   0.06303  -0.0147   0.1609   1.0000
  14.750   1.1385   0.07278   0.06643  -0.0154   0.1503   1.0000
  15.000   1.1368   0.07615   0.06983  -0.0161   0.1405   1.0000
  15.250   1.1349   0.07956   0.07322  -0.0170   0.1314   1.0000
  15.500   1.1329   0.08312   0.07681  -0.0179   0.1225   1.0000
  15.750   1.1315   0.08669   0.08042  -0.0189   0.1143   1.0000
  16.000   1.1289   0.09039   0.08409  -0.0201   0.1071   1.0000
  16.250   1.1281   0.09403   0.08784  -0.0212   0.0997   1.0000
  16.500   1.1256   0.09785   0.09163  -0.0226   0.0935   1.0000
  16.750   1.1247   0.10162   0.09553  -0.0239   0.0870   1.0000
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