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EPPLER 655 AIRFOIL (e655-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 655 AIRFOIL (e655-il)
Reynolds number: 50,000
Max Cl/Cd: 14.62 at α=12.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e655-il-50000-n5.txt
Download as CSV file: xf-e655-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 655 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.2446   0.11480   0.10812  -0.0831   0.9499   0.0524
 -11.750  -0.2394   0.10922   0.10254  -0.0877   0.9448   0.0531
 -11.500  -0.2375   0.10306   0.09638  -0.0926   0.9396   0.0529
 -11.000  -0.3032   0.07742   0.07058  -0.1130   0.9269   0.0494
 -10.750  -0.3238   0.07128   0.06429  -0.1177   0.9179   0.0492
 -10.500  -0.3403   0.06588   0.05866  -0.1218   0.9109   0.0491
 -10.250  -0.3614   0.06241   0.05497  -0.1222   0.9011   0.0491
 -10.000  -0.3792   0.05899   0.05124  -0.1221   0.8938   0.0492
  -9.750  -0.3995   0.05710   0.04911  -0.1189   0.8843   0.0494
  -9.500  -0.3994   0.05465   0.04648  -0.1181   0.8788   0.0502
  -9.250  -0.4012   0.05306   0.04473  -0.1159   0.8724   0.0513
  -9.000  -0.4019   0.05165   0.04317  -0.1137   0.8661   0.0530
  -8.750  -0.3978   0.04953   0.04069  -0.1124   0.8617   0.0552
  -8.500  -0.4011   0.04783   0.03859  -0.1093   0.8561   0.0572
  -8.250  -0.3978   0.04642   0.03698  -0.1067   0.8505   0.0593
  -8.000  -0.3824   0.04505   0.03549  -0.1059   0.8467   0.0626
  -7.750  -0.3635   0.04320   0.03316  -0.1054   0.8437   0.0678
  -7.250  -0.3507   0.04184   0.03171  -0.1000   0.8339   0.0752
  -7.000  -0.3312   0.04068   0.03037  -0.0991   0.8306   0.0818
  -6.750  -0.3068   0.03961   0.02910  -0.0989   0.8279   0.0909
  -6.500  -0.2924   0.03895   0.02849  -0.0972   0.8243   0.0989
  -6.250  -0.2903   0.03877   0.02818  -0.0935   0.8190   0.1065
  -6.000  -0.2758   0.03824   0.02761  -0.0918   0.8154   0.1184
  -5.750  -0.2557   0.03753   0.02690  -0.0910   0.8125   0.1352
  -5.500  -0.2334   0.03672   0.02619  -0.0906   0.8101   0.1570
  -5.250  -0.2380   0.03678   0.02630  -0.0862   0.8045   0.1708
  -5.000  -0.2331   0.03652   0.02611  -0.0832   0.8001   0.1934
  -4.750  -0.2181   0.03596   0.02570  -0.0819   0.7968   0.2298
  -4.500  -0.1981   0.03523   0.02523  -0.0814   0.7941   0.2825
  -4.250  -0.1888   0.03485   0.02514  -0.0793   0.7905   0.3371
  -4.000  -0.1916   0.03490   0.02548  -0.0751   0.7852   0.3865
  -3.750  -0.1806   0.03477   0.02580  -0.0723   0.7815   0.4683
  -3.500  -0.1650   0.03518   0.02663  -0.0687   0.7786   0.5544
  -3.250  -0.1437   0.03587   0.02733  -0.0660   0.7762   0.6233
  -3.000  -0.1459   0.03672   0.02813  -0.0611   0.7709   0.6599
  -2.750  -0.1379   0.03747   0.02874  -0.0575   0.7664   0.6953
  -2.500  -0.1224   0.03813   0.02925  -0.0546   0.7629   0.7268
  -2.250  -0.1026   0.03868   0.02962  -0.0524   0.7601   0.7559
  -2.000  -0.0943   0.03936   0.03019  -0.0486   0.7562   0.7775
  -1.750  -0.0925   0.03998   0.03073  -0.0442   0.7508   0.7977
  -1.500  -0.0787   0.04041   0.03101  -0.0415   0.7469   0.8193
  -1.250  -0.0588   0.04073   0.03118  -0.0395   0.7439   0.8397
  -1.000  -0.0359   0.04105   0.03134  -0.0380   0.7412   0.8586
  -0.750  -0.0385   0.04159   0.03183  -0.0338   0.7346   0.8759
  -0.500  -0.0179   0.04193   0.03204  -0.0327   0.7306   0.8938
  -0.250   0.0138   0.04223   0.03218  -0.0334   0.7275   0.9105
   0.000   0.0548   0.04254   0.03231  -0.0358   0.7252   0.9245
   0.250   0.0672   0.04325   0.03296  -0.0352   0.7182   0.9385
   0.500   0.1036   0.04376   0.03333  -0.0379   0.7140   0.9494
   0.750   0.1453   0.04415   0.03357  -0.0412   0.7107   0.9586
   1.000   0.1959   0.04451   0.03378  -0.0459   0.7083   0.9646
   1.250   0.2104   0.04552   0.03476  -0.0467   0.7001   0.9744
   1.500   0.2487   0.04600   0.03514  -0.0498   0.6958   0.9816
   1.750   0.2926   0.04635   0.03539  -0.0534   0.6927   0.9878
   2.000   0.3054   0.04730   0.03634  -0.0537   0.6848   1.0000
   2.250   0.3111   0.04747   0.03645  -0.0510   0.6791   1.0000
   2.500   0.3308   0.04750   0.03640  -0.0501   0.6757   1.0000
   2.750   0.3102   0.04814   0.03703  -0.0446   0.6657   1.0000
   3.000   0.3317   0.04839   0.03721  -0.0443   0.6612   1.0000
   3.250   0.3395   0.04910   0.03788  -0.0428   0.6539   1.0000
   3.500   0.3571   0.04969   0.03843  -0.0426   0.6474   1.0000
   3.750   0.3889   0.05000   0.03869  -0.0437   0.6437   1.0000
   4.000   0.3937   0.05113   0.03980  -0.0425   0.6340   1.0000
   4.250   0.4230   0.05157   0.04021  -0.0434   0.6292   1.0000
   4.500   0.4368   0.05256   0.04119  -0.0430   0.6210   1.0000
   4.750   0.4613   0.05317   0.04179  -0.0436   0.6147   1.0000
   5.000   0.4967   0.05338   0.04198  -0.0449   0.6112   1.0000
   5.250   0.5015   0.05478   0.04339  -0.0439   0.6001   1.0000
   5.500   0.5358   0.05498   0.04360  -0.0450   0.5962   1.0000
   5.750   0.5421   0.05640   0.04504  -0.0443   0.5851   1.0000
   6.000   0.5763   0.05653   0.04519  -0.0452   0.5810   1.0000
   6.250   0.5830   0.05799   0.04669  -0.0445   0.5698   1.0000
   6.500   0.6172   0.05803   0.04676  -0.0454   0.5656   1.0000
   6.750   0.6238   0.05955   0.04832  -0.0447   0.5541   1.0000
   7.000   0.6588   0.05943   0.04826  -0.0454   0.5501   1.0000
   7.250   0.6644   0.06107   0.04995  -0.0447   0.5381   1.0000
   7.750   0.7055   0.06248   0.05148  -0.0447   0.5219   1.0000
   8.000   0.7162   0.06391   0.05298  -0.0442   0.5111   1.0000
   8.250   0.7469   0.06379   0.05295  -0.0445   0.5056   1.0000
   8.500   0.7549   0.06545   0.05467  -0.0440   0.4938   1.0000
   8.750   0.7887   0.06496   0.05429  -0.0442   0.4892   1.0000
   9.000   0.7948   0.06679   0.05620  -0.0437   0.4767   1.0000
   9.500   0.8358   0.06792   0.05752  -0.0432   0.4597   1.0000
   9.750   0.8444   0.06964   0.05935  -0.0428   0.4479   1.0000
  10.000   0.8776   0.06877   0.05860  -0.0426   0.4429   1.0000
  10.250   0.8836   0.07077   0.06070  -0.0421   0.4302   1.0000
  10.500   0.9203   0.06927   0.05934  -0.0418   0.4262   1.0000
  10.750   0.9245   0.07148   0.06166  -0.0413   0.4129   1.0000
  11.250   0.9676   0.07175   0.06218  -0.0404   0.3958   1.0000
  11.750   1.0143   0.07146   0.06215  -0.0393   0.3786   1.0000
  12.000   1.0167   0.07399   0.06479  -0.0389   0.3652   1.0000
  12.500   1.0675   0.07303   0.06408  -0.0376   0.3472   1.0000
  12.750   1.0690   0.07573   0.06689  -0.0373   0.3338   1.0000
  13.000   1.0752   0.07786   0.06913  -0.0370   0.3215   1.0000
  13.250   1.1044   0.07678   0.06815  -0.0362   0.3122   1.0000
  13.500   1.1237   0.07703   0.06850  -0.0356   0.3010   1.0000
  13.750   1.1242   0.07996   0.07155  -0.0355   0.2883   1.0000
  14.000   1.1334   0.08172   0.07340  -0.0353   0.2767   1.0000
  14.250   1.1575   0.08128   0.07300  -0.0345   0.2659   1.0000
  14.500   1.1674   0.08288   0.07468  -0.0342   0.2542   1.0000
  14.750   1.1616   0.08689   0.07882  -0.0346   0.2426   1.0000
  15.000   1.1687   0.08900   0.08100  -0.0346   0.2318   1.0000
  15.250   1.1886   0.08909   0.08107  -0.0339   0.2211   1.0000
  15.500   1.1795   0.09377   0.08592  -0.0348   0.2107   1.0000
  15.750   1.1781   0.09731   0.08958  -0.0354   0.2009   1.0000
  16.000   1.1957   0.09771   0.08994  -0.0349   0.1911   1.0000
  16.250   1.1801   0.10371   0.09616  -0.0366   0.1822   1.0000
  16.500   1.1836   0.10655   0.09905  -0.0372   0.1735   1.0000
  16.750   1.1884   0.10914   0.10170  -0.0377   0.1649   1.0000
  17.000   1.1738   0.11537   0.10810  -0.0400   0.1576   1.0000
  17.250   1.1937   0.11519   0.10787  -0.0394   0.1493   1.0000
  17.500   1.1614   0.12504   0.11800  -0.0437   0.1436   1.0000
  17.750   1.1824   0.12452   0.11745  -0.0431   0.1358   1.0000
  18.000   1.1443   0.13611   0.12927  -0.0487   0.1310   1.0000
  18.250   1.1197   0.14546   0.13875  -0.0535   0.1253   1.0000
  18.500   1.1336   0.14629   0.13962  -0.0538   0.1195   1.0000
  18.750   1.0633   0.16792   0.16125  -0.0660   0.1132   1.0000
  19.000   1.1277   0.15571   0.14917  -0.0588   0.1089   1.0000
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