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EPPLER 548 AIRFOIL (e548-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 548 AIRFOIL (e548-il)
Reynolds number: 500,000
Max Cl/Cd: 90.66 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e548-il-500000-n5.txt
Download as CSV file: xf-e548-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 548 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.500  -0.6654   0.10054   0.09781  -0.0358   1.0000   0.0039
 -15.250  -0.7013   0.08676   0.08384  -0.0439   1.0000   0.0038
 -15.000  -0.7268   0.07694   0.07383  -0.0500   1.0000   0.0037
 -14.750  -0.7535   0.06844   0.06511  -0.0547   1.0000   0.0037
 -14.500  -0.7728   0.06220   0.05868  -0.0574   1.0000   0.0037
 -14.250  -0.7878   0.05723   0.05354  -0.0589   1.0000   0.0037
 -14.000  -0.8025   0.05273   0.04883  -0.0596   1.0000   0.0037
 -13.750  -0.8124   0.04916   0.04509  -0.0596   1.0000   0.0037
 -13.500  -0.8246   0.04545   0.04115  -0.0591   1.0000   0.0037
 -13.250  -0.8291   0.04272   0.03826  -0.0583   1.0000   0.0037
 -13.000  -0.8310   0.04033   0.03571  -0.0573   1.0000   0.0037
 -12.750  -0.8316   0.03810   0.03332  -0.0561   1.0000   0.0038
 -12.500  -0.8309   0.03601   0.03107  -0.0547   1.0000   0.0038
 -12.250  -0.8269   0.03431   0.02924  -0.0533   1.0000   0.0038
 -12.000  -0.8224   0.03264   0.02742  -0.0518   1.0000   0.0039
 -11.750  -0.8160   0.03120   0.02588  -0.0502   1.0000   0.0039
 -11.500  -0.8090   0.02977   0.02430  -0.0485   1.0000   0.0040
 -11.000  -0.6999   0.02539   0.01951  -0.0649   0.9116   0.0042
 -10.750  -0.6453   0.02402   0.01776  -0.0726   0.8364   0.0045
 -10.500  -0.6326   0.02335   0.01684  -0.0710   0.7950   0.0044
 -10.250  -0.6196   0.02271   0.01604  -0.0694   0.7668   0.0047
 -10.000  -0.6062   0.02207   0.01524  -0.0678   0.7447   0.0048
  -9.750  -0.5927   0.02140   0.01444  -0.0662   0.7255   0.0049
  -9.250  -0.5634   0.02019   0.01299  -0.0633   0.6938   0.0052
  -9.000  -0.5483   0.01960   0.01229  -0.0619   0.6791   0.0057
  -8.750  -0.5329   0.01904   0.01162  -0.0604   0.6674   0.0058
  -8.500  -0.5177   0.01849   0.01099  -0.0589   0.6565   0.0059
  -8.250  -0.5027   0.01792   0.01034  -0.0574   0.6463   0.0061
  -8.000  -0.4877   0.01737   0.00973  -0.0558   0.6371   0.0064
  -7.750  -0.4721   0.01690   0.00918  -0.0543   0.6280   0.0069
  -7.500  -0.4566   0.01642   0.00864  -0.0526   0.6199   0.0076
  -7.250  -0.4414   0.01599   0.00813  -0.0509   0.6114   0.0079
  -7.000  -0.4277   0.01556   0.00766  -0.0489   0.6037   0.0085
  -6.750  -0.4146   0.01523   0.00727  -0.0466   0.5961   0.0094
  -6.500  -0.3997   0.01491   0.00691  -0.0446   0.5893   0.0112
  -6.250  -0.3816   0.01459   0.00654  -0.0432   0.5826   0.0127
  -6.000  -0.3636   0.01426   0.00618  -0.0417   0.5764   0.0154
  -5.750  -0.3447   0.01392   0.00583  -0.0404   0.5709   0.0201
  -5.500  -0.3251   0.01359   0.00551  -0.0393   0.5652   0.0279
  -5.250  -0.3054   0.01327   0.00521  -0.0381   0.5599   0.0395
  -5.000  -0.2851   0.01291   0.00491  -0.0371   0.5551   0.0564
  -4.750  -0.2649   0.01253   0.00462  -0.0361   0.5498   0.0812
  -4.500  -0.2448   0.01213   0.00433  -0.0350   0.5447   0.1159
  -4.250  -0.2260   0.01159   0.00401  -0.0339   0.5404   0.1720
  -4.000  -0.2105   0.01070   0.00356  -0.0325   0.5362   0.2786
  -3.500  -0.1795   0.00872   0.00280  -0.0295   0.5284   0.5914
  -3.250  -0.1518   0.00878   0.00284  -0.0295   0.5248   0.6212
  -3.000  -0.1235   0.00888   0.00291  -0.0295   0.5212   0.6404
  -2.750  -0.0952   0.00902   0.00300  -0.0296   0.5173   0.6557
  -2.500  -0.0670   0.00922   0.00315  -0.0295   0.5134   0.6674
  -2.000  -0.0104   0.00955   0.00340  -0.0295   0.5068   0.6820
  -1.750   0.0184   0.00954   0.00332  -0.0298   0.5037   0.6833
  -1.500   0.0472   0.00954   0.00324  -0.0301   0.5006   0.6846
  -1.250   0.0758   0.00955   0.00317  -0.0304   0.4977   0.6858
  -1.000   0.1043   0.00956   0.00312  -0.0307   0.4948   0.6868
  -0.750   0.1328   0.00957   0.00308  -0.0309   0.4921   0.6876
  -0.500   0.1617   0.00957   0.00306  -0.0312   0.4892   0.6885
  -0.250   0.1904   0.00958   0.00304  -0.0315   0.4864   0.6894
   0.000   0.2190   0.00960   0.00304  -0.0318   0.4838   0.6904
   0.250   0.2475   0.00964   0.00304  -0.0320   0.4813   0.6915
   0.500   0.2758   0.00968   0.00304  -0.0323   0.4788   0.6925
   0.750   0.3043   0.00973   0.00305  -0.0326   0.4764   0.6934
   1.000   0.3330   0.00974   0.00307  -0.0329   0.4739   0.6944
   1.250   0.3617   0.00977   0.00309  -0.0332   0.4715   0.6955
   1.500   0.3903   0.00981   0.00312  -0.0335   0.4691   0.6965
   1.750   0.4187   0.00985   0.00314  -0.0338   0.4666   0.6975
   2.000   0.4470   0.00991   0.00318  -0.0340   0.4641   0.6986
   2.250   0.4752   0.00999   0.00322  -0.0343   0.4617   0.6999
   2.500   0.5037   0.01005   0.00328  -0.0346   0.4597   0.7010
   2.750   0.5323   0.01009   0.00333  -0.0349   0.4572   0.7021
   3.000   0.5606   0.01013   0.00340  -0.0352   0.4546   0.7029
   3.250   0.5887   0.01018   0.00346  -0.0355   0.4520   0.7039
   3.500   0.6166   0.01024   0.00354  -0.0357   0.4493   0.7048
   3.750   0.6443   0.01032   0.00362  -0.0358   0.4466   0.7058
   4.000   0.6721   0.01040   0.00372  -0.0360   0.4438   0.7068
   4.250   0.7002   0.01044   0.00381  -0.0362   0.4405   0.7078
   4.500   0.7279   0.01050   0.00391  -0.0364   0.4367   0.7089
   4.750   0.7553   0.01058   0.00401  -0.0365   0.4331   0.7100
   5.000   0.7824   0.01069   0.00411  -0.0366   0.4297   0.7112
   5.250   0.8101   0.01076   0.00424  -0.0368   0.4262   0.7125
   5.500   0.8376   0.01083   0.00436  -0.0370   0.4217   0.7140
   5.750   0.8645   0.01092   0.00447  -0.0370   0.4171   0.7154
   6.000   0.8910   0.01103   0.00459  -0.0370   0.4127   0.7167
   6.250   0.9184   0.01111   0.00473  -0.0372   0.4078   0.7179
   6.500   0.9449   0.01121   0.00487  -0.0372   0.4020   0.7190
   6.750   0.9707   0.01132   0.00501  -0.0370   0.3965   0.7202
   7.000   0.9970   0.01141   0.00517  -0.0370   0.3894   0.7214
   7.250   1.0218   0.01155   0.00534  -0.0367   0.3815   0.7227
   7.500   1.0471   0.01168   0.00552  -0.0365   0.3717   0.7240
   7.750   1.0712   0.01185   0.00572  -0.0361   0.3607   0.7254
   8.000   1.0943   0.01207   0.00595  -0.0356   0.3478   0.7269
   8.250   1.1159   0.01236   0.00622  -0.0348   0.3313   0.7285
   8.500   1.1349   0.01275   0.00656  -0.0336   0.3105   0.7302
   8.750   1.1513   0.01326   0.00698  -0.0320   0.2874   0.7320
   9.250   1.1759   0.01454   0.00807  -0.0277   0.2386   0.7357
   9.500   1.1827   0.01516   0.00863  -0.0245   0.2187   0.7375
   9.750   1.1886   0.01584   0.00927  -0.0212   0.2010   0.7394
  10.000   1.1943   0.01659   0.00999  -0.0182   0.1841   0.7414
  10.250   1.1982   0.01743   0.01080  -0.0150   0.1678   0.7435
  10.500   1.2008   0.01838   0.01172  -0.0120   0.1534   0.7459
  10.750   1.2028   0.01944   0.01277  -0.0092   0.1414   0.7482
  11.000   1.2031   0.02072   0.01403  -0.0066   0.1297   0.7506
  11.250   1.2046   0.02207   0.01539  -0.0045   0.1196   0.7529
  11.500   1.2058   0.02357   0.01693  -0.0027   0.1106   0.7553
  11.750   1.2054   0.02533   0.01871  -0.0011   0.1023   0.7580
  12.000   1.2047   0.02725   0.02066   0.0003   0.0935   0.7608
  12.250   1.2050   0.02921   0.02266   0.0014   0.0862   0.7638
  12.500   1.2030   0.03146   0.02492   0.0024   0.0793   0.7671
  12.750   1.2025   0.03366   0.02715   0.0031   0.0722   0.7701
  13.000   1.2017   0.03593   0.02947   0.0038   0.0669   0.7735
  13.250   1.1999   0.03835   0.03193   0.0044   0.0609   0.7771
  13.500   1.1991   0.04075   0.03438   0.0048   0.0558   0.7807
  13.750   1.1972   0.04332   0.03697   0.0051   0.0511   0.7843
  14.000   1.1972   0.04575   0.03947   0.0053   0.0468   0.7881
  14.500   1.1967   0.05095   0.04478   0.0053   0.0392   0.7970
  15.000   1.1969   0.05636   0.05031   0.0049   0.0327   0.8068
  15.250   1.1968   0.05918   0.05318   0.0045   0.0303   0.8129
  15.500   1.1981   0.06191   0.05601   0.0041   0.0277   0.8192
  15.750   1.1986   0.06475   0.05892   0.0036   0.0256   0.8269
  16.000   1.1995   0.06763   0.06190   0.0030   0.0239   0.8357
  16.250   1.1995   0.07061   0.06497   0.0024   0.0215   0.8468
  16.500   1.1995   0.07356   0.06804   0.0019   0.0201   0.8628
  16.750   1.1996   0.07648   0.07113   0.0013   0.0184   0.8950
  17.000   1.2047   0.08005   0.07486  -0.0013   0.0168   1.0000
  17.250   1.2059   0.08324   0.07812  -0.0024   0.0159   1.0000
  17.500   1.2049   0.08677   0.08169  -0.0036   0.0143   1.0000
  17.750   1.2050   0.09024   0.08524  -0.0049   0.0132   1.0000
  18.000   1.2048   0.09378   0.08883  -0.0063   0.0121   1.0000
  18.250   1.2029   0.09765   0.09276  -0.0078   0.0114   1.0000
  18.500   1.2029   0.10124   0.09644  -0.0093   0.0107   1.0000
  18.750   1.2020   0.10504   0.10032  -0.0110   0.0101   1.0000
  19.000   1.1986   0.10927   0.10460  -0.0129   0.0090   1.0000
  19.250   1.1980   0.11310   0.10851  -0.0146   0.0086   1.0000
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