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EPPLER 550 AIRFOIL (e550-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 550 AIRFOIL (e550-il)
Reynolds number: 200,000
Max Cl/Cd: 65.98 at α=10.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e550-il-200000.txt
Download as CSV file: xf-e550-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.5452   0.05961   0.05552  -0.0702   1.0000   0.0266
 -12.000  -0.5530   0.05549   0.05136  -0.0701   1.0000   0.0262
 -11.750  -0.6544   0.06075   0.05616  -0.0685   1.0000   0.0265
 -11.500  -0.6632   0.05711   0.05246  -0.0677   1.0000   0.0262
 -11.250  -0.6692   0.05415   0.04944  -0.0666   1.0000   0.0257
 -11.000  -0.6807   0.05125   0.04642  -0.0650   1.0000   0.0250
 -10.750  -0.7536   0.04678   0.04120  -0.0564   1.0000   0.0226
 -10.500  -0.7652   0.04533   0.03955  -0.0521   1.0000   0.0224
 -10.250  -0.7601   0.04257   0.03674  -0.0500   1.0000   0.0222
 -10.000  -0.7584   0.04034   0.03433  -0.0480   0.9979   0.0221
  -9.750  -0.7282   0.03710   0.03058  -0.0516   0.9842   0.0224
  -9.500  -0.6901   0.03463   0.02829  -0.0548   0.9711   0.0240
  -9.250  -0.6544   0.03212   0.02552  -0.0575   0.9538   0.0248
  -9.000  -0.6082   0.02946   0.02254  -0.0612   0.9415   0.0252
  -8.750  -0.5541   0.02714   0.01996  -0.0655   0.9282   0.0261
  -8.500  -0.4926   0.02518   0.01796  -0.0705   0.9139   0.0280
  -8.250  -0.4357   0.02377   0.01645  -0.0760   0.8879   0.0312
  -8.000  -0.3979   0.02258   0.01519  -0.0791   0.8554   0.0360
  -7.750  -0.3809   0.02152   0.01401  -0.0784   0.8270   0.0404
  -7.500  -0.3709   0.02071   0.01304  -0.0763   0.8032   0.0452
  -7.250  -0.3707   0.01979   0.01208  -0.0731   0.7840   0.0511
  -7.000  -0.3674   0.01895   0.01118  -0.0700   0.7680   0.0623
  -6.750  -0.3642   0.01791   0.01020  -0.0670   0.7543   0.0816
  -6.500  -0.3600   0.01675   0.00924  -0.0643   0.7427   0.1255
  -6.250  -0.3589   0.01518   0.00821  -0.0616   0.7311   0.2238
  -6.000  -0.3612   0.01339   0.00764  -0.0582   0.7213   0.4464
  -5.750  -0.3365   0.01397   0.00824  -0.0570   0.7117   0.5350
  -5.500  -0.3096   0.01479   0.00897  -0.0560   0.7017   0.5629
  -5.250  -0.2817   0.01559   0.00961  -0.0550   0.6937   0.5807
  -5.000  -0.2538   0.01635   0.01032  -0.0540   0.6847   0.5930
  -4.750  -0.2261   0.01697   0.01080  -0.0532   0.6778   0.6048
  -4.500  -0.1982   0.01770   0.01147  -0.0522   0.6703   0.6151
  -4.250  -0.1701   0.01833   0.01203  -0.0512   0.6637   0.6229
  -4.000  -0.1427   0.01892   0.01250  -0.0504   0.6577   0.6330
  -3.750  -0.1132   0.02022   0.01385  -0.0482   0.6509   0.6416
  -3.500  -0.0877   0.02054   0.01403  -0.0475   0.6454   0.6532
  -3.250  -0.0600   0.02085   0.01429  -0.0466   0.6400   0.6559
  -3.000  -0.0337   0.02085   0.01423  -0.0463   0.6345   0.6591
  -2.750  -0.0079   0.02059   0.01382  -0.0465   0.6299   0.6637
  -2.500   0.0173   0.02003   0.01307  -0.0476   0.6258   0.6691
  -2.250   0.0432   0.01995   0.01299  -0.0472   0.6207   0.6708
  -2.000   0.0699   0.01988   0.01286  -0.0470   0.6160   0.6727
  -1.750   0.0972   0.01979   0.01266  -0.0472   0.6120   0.6751
  -1.500   0.1241   0.01964   0.01243  -0.0475   0.6082   0.6776
  -1.250   0.1504   0.01941   0.01215  -0.0480   0.6039   0.6809
  -1.000   0.1783   0.01909   0.01172  -0.0491   0.6001   0.6839
  -0.750   0.2062   0.01891   0.01145  -0.0496   0.5966   0.6862
  -0.500   0.2343   0.01892   0.01137  -0.0498   0.5936   0.6878
  -0.250   0.2600   0.01885   0.01134  -0.0498   0.5894   0.6893
   0.000   0.2870   0.01879   0.01128  -0.0500   0.5856   0.6910
   0.250   0.3147   0.01875   0.01120  -0.0503   0.5824   0.6932
   0.500   0.3434   0.01872   0.01109  -0.0509   0.5796   0.6957
   0.750   0.3727   0.01871   0.01099  -0.0518   0.5768   0.6980
   1.000   0.3996   0.01864   0.01095  -0.0524   0.5729   0.7003
   1.250   0.4273   0.01861   0.01091  -0.0529   0.5693   0.7022
   1.500   0.4544   0.01863   0.01094  -0.0530   0.5663   0.7038
   1.750   0.4823   0.01868   0.01098  -0.0532   0.5636   0.7058
   2.000   0.5113   0.01880   0.01104  -0.0537   0.5610   0.7079
   2.250   0.5369   0.01890   0.01123  -0.0538   0.5575   0.7099
   2.500   0.5635   0.01900   0.01138  -0.0540   0.5541   0.7121
   2.750   0.5914   0.01906   0.01145  -0.0545   0.5508   0.7145
   3.000   0.6208   0.01911   0.01146  -0.0553   0.5478   0.7169
   3.250   0.6502   0.01921   0.01152  -0.0559   0.5453   0.7191
   3.500   0.6753   0.01941   0.01182  -0.0557   0.5421   0.7212
   3.750   0.6998   0.01959   0.01211  -0.0555   0.5382   0.7236
   4.000   0.7265   0.01972   0.01229  -0.0556   0.5347   0.7260
   4.250   0.7552   0.01979   0.01237  -0.0561   0.5315   0.7286
   4.500   0.7855   0.01992   0.01245  -0.0569   0.5287   0.7313
   4.750   0.8102   0.02017   0.01280  -0.0569   0.5246   0.7342
   5.000   0.8345   0.02032   0.01307  -0.0566   0.5202   0.7364
   5.250   0.8616   0.02039   0.01319  -0.0567   0.5165   0.7390
   5.500   0.8911   0.02044   0.01325  -0.0571   0.5133   0.7421
   5.750   0.9160   0.02069   0.01359  -0.0570   0.5091   0.7456
   6.000   0.9401   0.02089   0.01390  -0.0568   0.5041   0.7492
   6.250   0.9683   0.02088   0.01394  -0.0571   0.4998   0.7522
   6.500   0.9988   0.02085   0.01389  -0.0576   0.4962   0.7551
   6.750   1.0190   0.02110   0.01434  -0.0566   0.4906   0.7586
   7.000   1.0448   0.02112   0.01444  -0.0565   0.4852   0.7626
   7.250   1.0769   0.02099   0.01426  -0.0574   0.4808   0.7669
   7.500   1.0974   0.02114   0.01459  -0.0563   0.4748   0.7705
   7.750   1.1215   0.02110   0.01467  -0.0558   0.4688   0.7750
   8.000   1.1539   0.02090   0.01442  -0.0566   0.4640   0.7803
   8.250   1.1714   0.02106   0.01480  -0.0551   0.4567   0.7852
   8.500   1.1976   0.02083   0.01464  -0.0548   0.4504   0.7900
   8.750   1.2202   0.02081   0.01473  -0.0541   0.4434   0.7959
   9.000   1.2426   0.02066   0.01469  -0.0532   0.4357   0.8018
   9.250   1.2635   0.02054   0.01468  -0.0521   0.4279   0.8081
   9.500   1.2842   0.02038   0.01462  -0.0510   0.4189   0.8160
   9.750   1.2991   0.02033   0.01476  -0.0488   0.4094   0.8238
  10.000   1.3184   0.02016   0.01464  -0.0474   0.3996   0.8335
  10.250   1.3284   0.02019   0.01485  -0.0445   0.3878   0.8447
  10.500   1.3368   0.02026   0.01508  -0.0414   0.3751   0.8577
  10.750   1.3407   0.02036   0.01530  -0.0375   0.3618   0.8752
  11.000   1.3403   0.02057   0.01563  -0.0329   0.3478   0.9057
  11.250   1.3456   0.02102   0.01615  -0.0304   0.3297   1.0000
  11.500   1.3477   0.02206   0.01706  -0.0281   0.3103   1.0000
  11.750   1.3451   0.02346   0.01840  -0.0256   0.2906   1.0000
  12.000   1.3392   0.02523   0.02009  -0.0231   0.2721   1.0000
  12.250   1.3308   0.02741   0.02219  -0.0210   0.2546   1.0000
  12.500   1.3217   0.02988   0.02460  -0.0192   0.2382   1.0000
  12.750   1.3123   0.03260   0.02727  -0.0179   0.2229   1.0000
  13.000   1.3029   0.03551   0.03013  -0.0168   0.2083   1.0000
  13.250   1.2939   0.03855   0.03313  -0.0161   0.1945   1.0000
  13.500   1.2850   0.04169   0.03625  -0.0155   0.1815   1.0000
  13.750   1.2766   0.04491   0.03944  -0.0152   0.1694   1.0000
  14.000   1.2683   0.04823   0.04273  -0.0150   0.1583   1.0000
  14.250   1.2597   0.05173   0.04617  -0.0150   0.1476   1.0000
  14.500   1.2543   0.05506   0.04952  -0.0152   0.1366   1.0000
  14.750   1.2492   0.05845   0.05291  -0.0155   0.1265   1.0000
  15.000   1.2429   0.06205   0.05647  -0.0159   0.1175   1.0000
  15.250   1.2380   0.06562   0.06002  -0.0165   0.1088   1.0000
  15.500   1.2348   0.06908   0.06352  -0.0171   0.1002   1.0000
  15.750   1.2295   0.07280   0.06718  -0.0178   0.0931   1.0000
  16.000   1.2273   0.07634   0.07078  -0.0186   0.0858   1.0000
  16.250   1.2243   0.07993   0.07436  -0.0195   0.0796   1.0000
  16.500   1.2216   0.08363   0.07809  -0.0205   0.0738   1.0000
  16.750   1.2200   0.08717   0.08164  -0.0214   0.0685   1.0000
  17.000   1.2181   0.09088   0.08540  -0.0226   0.0637   1.0000
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