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EPPLER 544 AIRFOIL (e544-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 544 AIRFOIL (e544-il)
Reynolds number: 100,000
Max Cl/Cd: 37.4 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e544-il-100000-n5.txt
Download as CSV file: xf-e544-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 544 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
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.4472   0.09746   0.09236  -0.0641   1.0000   0.0183
 -12.500  -0.4771   0.08706   0.08190  -0.0699   1.0000   0.0179
 -12.250  -0.5502   0.07309   0.06751  -0.0756   1.0000   0.0160
 -12.000  -0.5739   0.06863   0.06289  -0.0757   1.0000   0.0161
 -11.750  -0.5920   0.06513   0.05928  -0.0748   1.0000   0.0160
 -11.500  -0.6096   0.06208   0.05611  -0.0733   1.0000   0.0160
 -11.250  -0.6281   0.05926   0.05317  -0.0709   1.0000   0.0159
 -11.000  -0.6536   0.05667   0.05038  -0.0673   1.0000   0.0161
 -10.750  -0.6736   0.05503   0.04868  -0.0629   1.0000   0.0161
 -10.500  -0.6810   0.05185   0.04516  -0.0622   0.9925   0.0162
 -10.250  -0.6718   0.04877   0.04184  -0.0635   0.9810   0.0164
 -10.000  -0.6583   0.04629   0.03916  -0.0645   0.9695   0.0169
  -9.750  -0.6439   0.04351   0.03604  -0.0650   0.9588   0.0171
  -9.500  -0.6245   0.04077   0.03295  -0.0656   0.9498   0.0175
  -9.250  -0.5952   0.03802   0.02984  -0.0672   0.9443   0.0180
  -9.000  -0.5596   0.03549   0.02697  -0.0690   0.9397   0.0188
  -8.750  -0.5214   0.03340   0.02457  -0.0706   0.9345   0.0197
  -8.500  -0.4861   0.03181   0.02291  -0.0726   0.9292   0.0212
  -8.250  -0.4530   0.03054   0.02150  -0.0741   0.9224   0.0236
  -8.000  -0.4226   0.02926   0.02019  -0.0754   0.9147   0.0262
  -7.750  -0.3931   0.02802   0.01880  -0.0764   0.9072   0.0292
  -7.500  -0.3689   0.02691   0.01768  -0.0768   0.8979   0.0334
  -7.250  -0.3468   0.02592   0.01664  -0.0768   0.8883   0.0394
  -7.000  -0.3248   0.02491   0.01560  -0.0767   0.8797   0.0498
  -6.750  -0.3087   0.02402   0.01479  -0.0755   0.8695   0.0669
  -6.500  -0.2895   0.02303   0.01403  -0.0748   0.8619   0.1060
  -6.250  -0.2830   0.02212   0.01349  -0.0721   0.8509   0.1669
  -6.000  -0.2888   0.02095   0.01278  -0.0678   0.8405   0.2509
  -5.750  -0.2498   0.02314   0.01676  -0.0639   0.8359   0.5515
  -5.500  -0.2528   0.02274   0.01621  -0.0597   0.8268   0.5916
  -5.250  -0.2521   0.02248   0.01578  -0.0560   0.8175   0.6215
  -5.000  -0.2461   0.02246   0.01557  -0.0527   0.8098   0.6460
  -4.750  -0.2184   0.02357   0.01650  -0.0512   0.8033   0.6631
  -4.500  -0.1833   0.02476   0.01748  -0.0506   0.7986   0.6791
  -4.250  -0.1454   0.02625   0.01882  -0.0500   0.7935   0.6950
  -4.000  -0.1259   0.02670   0.01913  -0.0480   0.7871   0.7087
  -3.750  -0.0872   0.02690   0.01913  -0.0492   0.7829   0.7112
  -3.500  -0.0591   0.02691   0.01899  -0.0492   0.7775   0.7145
  -3.000  -0.0284   0.02625   0.01806  -0.0461   0.7662   0.7263
  -2.750  -0.0033   0.02621   0.01791  -0.0457   0.7610   0.7287
  -2.500   0.0187   0.02609   0.01770  -0.0450   0.7555   0.7318
  -2.250   0.0377   0.02577   0.01725  -0.0441   0.7509   0.7363
  -2.000   0.0473   0.02536   0.01675  -0.0419   0.7454   0.7417
  -1.750   0.0705   0.02530   0.01663  -0.0413   0.7402   0.7436
  -1.500   0.0955   0.02516   0.01640  -0.0411   0.7362   0.7459
  -1.250   0.1214   0.02493   0.01606  -0.0412   0.7328   0.7483
  -1.000   0.1320   0.02478   0.01589  -0.0389   0.7265   0.7523
  -0.750   0.1448   0.02436   0.01538  -0.0375   0.7216   0.7568
  -0.500   0.1726   0.02424   0.01520  -0.0377   0.7184   0.7581
  -0.250   0.1948   0.02420   0.01513  -0.0370   0.7140   0.7598
   0.000   0.2134   0.02416   0.01507  -0.0359   0.7087   0.7616
   0.250   0.2370   0.02403   0.01490  -0.0356   0.7047   0.7637
   0.500   0.2633   0.02387   0.01467  -0.0358   0.7017   0.7660
   0.750   0.2785   0.02382   0.01463  -0.0344   0.6964   0.7687
   1.000   0.2972   0.02368   0.01448  -0.0337   0.6915   0.7712
   1.250   0.3226   0.02355   0.01431  -0.0339   0.6879   0.7732
   1.500   0.3521   0.02345   0.01418  -0.0344   0.6850   0.7745
   1.750   0.3655   0.02363   0.01443  -0.0324   0.6789   0.7763
   2.000   0.3882   0.02363   0.01445  -0.0320   0.6744   0.7778
   2.250   0.4163   0.02352   0.01433  -0.0325   0.6710   0.7792
   2.500   0.4400   0.02352   0.01434  -0.0323   0.6669   0.7810
   2.750   0.4557   0.02367   0.01455  -0.0309   0.6607   0.7834
   3.000   0.4827   0.02359   0.01448  -0.0313   0.6565   0.7856
   3.250   0.5153   0.02341   0.01429  -0.0326   0.6533   0.7874
   3.500   0.5265   0.02368   0.01466  -0.0304   0.6460   0.7892
   3.750   0.5524   0.02364   0.01468  -0.0304   0.6412   0.7904
   4.000   0.5854   0.02347   0.01452  -0.0314   0.6376   0.7916
   4.250   0.5957   0.02379   0.01496  -0.0290   0.6299   0.7934
   4.500   0.6230   0.02372   0.01494  -0.0292   0.6248   0.7951
   4.750   0.6547   0.02357   0.01484  -0.0301   0.6205   0.7970
   5.000   0.6658   0.02386   0.01525  -0.0278   0.6121   0.7996
   5.250   0.6989   0.02364   0.01507  -0.0290   0.6071   0.8014
   5.500   0.7145   0.02385   0.01540  -0.0275   0.5990   0.8036
   5.750   0.7422   0.02371   0.01533  -0.0277   0.5925   0.8050
   6.000   0.7603   0.02380   0.01553  -0.0263   0.5848   0.8066
   6.250   0.7841   0.02371   0.01555  -0.0257   0.5770   0.8083
   6.500   0.8012   0.02380   0.01576  -0.0242   0.5683   0.8104
   6.750   0.8282   0.02360   0.01565  -0.0241   0.5599   0.8125
   7.000   0.8386   0.02382   0.01601  -0.0216   0.5493   0.8154
   7.250   0.8613   0.02371   0.01598  -0.0209   0.5394   0.8180
   7.500   0.8792   0.02367   0.01604  -0.0194   0.5284   0.8204
   7.750   0.8838   0.02392   0.01642  -0.0159   0.5160   0.8226
   8.000   0.8944   0.02414   0.01677  -0.0134   0.5027   0.8251
   8.250   0.9065   0.02438   0.01711  -0.0112   0.4879   0.8278
   8.500   0.9193   0.02466   0.01748  -0.0094   0.4718   0.8307
   8.750   0.9331   0.02495   0.01781  -0.0077   0.4535   0.8338
   9.000   0.9458   0.02529   0.01819  -0.0059   0.4332   0.8368
   9.250   0.9541   0.02584   0.01876  -0.0035   0.4108   0.8400
   9.500   0.9649   0.02639   0.01926  -0.0016   0.3871   0.8435
   9.750   0.9724   0.02722   0.02005   0.0003   0.3619   0.8474
  10.000   0.9788   0.02823   0.02099   0.0022   0.3371   0.8511
  10.250   0.9826   0.02937   0.02207   0.0044   0.3137   0.8545
  10.500   0.9858   0.03066   0.02334   0.0063   0.2909   0.8585
  10.750   0.9887   0.03210   0.02474   0.0079   0.2687   0.8630
  11.000   0.9909   0.03365   0.02625   0.0095   0.2478   0.8674
  11.250   0.9927   0.03523   0.02783   0.0111   0.2276   0.8723
  11.500   0.9947   0.03693   0.02952   0.0124   0.2087   0.8781
  11.750   0.9962   0.03871   0.03128   0.0137   0.1912   0.8843
  12.250   0.9998   0.04242   0.03504   0.0157   0.1593   0.9004
  12.500   1.0022   0.04440   0.03706   0.0164   0.1448   0.9117
  12.750   1.0053   0.04651   0.03921   0.0166   0.1310   0.9269
  13.000   1.0075   0.04853   0.04131   0.0166   0.1186   0.9728
  13.250   1.0113   0.05084   0.04365   0.0164   0.1070   1.0000
  13.500   1.0152   0.05330   0.04613   0.0161   0.0967   1.0000
  13.750   1.0178   0.05593   0.04877   0.0158   0.0880   1.0000
  14.000   1.0192   0.05873   0.05159   0.0154   0.0803   1.0000
  14.250   1.0228   0.06136   0.05431   0.0150   0.0731   1.0000
  14.500   1.0218   0.06452   0.05742   0.0145   0.0676   1.0000
  14.750   1.0256   0.06727   0.06031   0.0140   0.0615   1.0000
  15.000   1.0238   0.07063   0.06366   0.0133   0.0573   1.0000
  15.250   1.0266   0.07358   0.06675   0.0126   0.0526   1.0000
  15.500   1.0258   0.07703   0.07025   0.0117   0.0490   1.0000
  15.750   1.0260   0.08037   0.07368   0.0108   0.0457   1.0000
  16.000   1.0261   0.08383   0.07725   0.0098   0.0424   1.0000
  16.250   1.0233   0.08772   0.08119   0.0084   0.0400   1.0000
  16.500   1.0240   0.09120   0.08481   0.0074   0.0375   1.0000
  16.750   1.0224   0.09513   0.08888   0.0059   0.0350   1.0000
  17.000   1.0196   0.09925   0.09304   0.0042   0.0332   1.0000
  17.250   1.0181   0.10321   0.09713   0.0027   0.0314   1.0000
  17.500   1.0157   0.10749   0.10158   0.0008   0.0296   1.0000
  17.750   1.0129   0.11183   0.10603  -0.0012   0.0282   1.0000
  18.000   1.0099   0.11621   0.11043  -0.0035   0.0269   1.0000
  18.250   1.0060   0.12095   0.11534  -0.0057   0.0257   1.0000
  18.500   0.9999   0.12622   0.12083  -0.0085   0.0246   1.0000
  18.750   0.9945   0.13141   0.12617  -0.0113   0.0237   1.0000
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