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EPPLER 59 AIRFOIL (e59-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 59 AIRFOIL (e59-il)
Reynolds number: 200,000
Max Cl/Cd: 99.6 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e59-il-200000-n5.txt
Download as CSV file: xf-e59-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 59 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2575   0.10942   0.10606  -0.0399   0.9885   0.0215
  -9.250  -0.2522   0.10623   0.10288  -0.0424   0.9873   0.0217
  -9.000  -0.2492   0.10322   0.09988  -0.0439   0.9848   0.0218
  -8.750  -0.2439   0.09982   0.09650  -0.0458   0.9827   0.0219
  -8.500  -0.2363   0.09613   0.09279  -0.0477   0.9808   0.0219
  -8.250  -0.2280   0.09220   0.08886  -0.0498   0.9793   0.0219
  -8.000  -0.2225   0.08868   0.08536  -0.0511   0.9767   0.0219
  -7.750  -0.2176   0.08516   0.08185  -0.0522   0.9735   0.0220
  -7.500  -0.2105   0.08126   0.07796  -0.0540   0.9710   0.0220
  -7.250  -0.2022   0.07722   0.07392  -0.0562   0.9690   0.0220
  -7.000  -0.2021   0.07420   0.07093  -0.0560   0.9640   0.0220
  -6.750  -0.1972   0.07046   0.06720  -0.0572   0.9602   0.0219
  -6.500  -0.1868   0.06537   0.06211  -0.0558   0.9592   0.0189
  -6.250  -0.1776   0.06104   0.05779  -0.0589   0.9563   0.0173
  -6.000  -0.2466   0.07799   0.07456  -0.0572   0.9615   0.0187
  -5.750  -0.2239   0.07309   0.06965  -0.0640   0.9583   0.0165
  -5.500  -0.2026   0.06728   0.06383  -0.0720   0.9531   0.0148
  -5.250  -0.1658   0.05930   0.05577  -0.0849   0.9483   0.0137
  -5.000  -0.1247   0.05314   0.04952  -0.0960   0.9460   0.0139
  -4.750  -0.0911   0.05090   0.04722  -0.1012   0.9445   0.0160
  -4.250   0.0438   0.03205   0.02751  -0.1348   0.9438   0.0167
  -4.000   0.1128   0.02301   0.01727  -0.1477   0.9452   0.0193
  -3.750   0.1579   0.02010   0.01355  -0.1520   0.9452   0.0220
  -3.500   0.1967   0.01861   0.01178  -0.1549   0.9446   0.0253
  -3.250   0.2317   0.01797   0.01087  -0.1565   0.9432   0.0309
  -3.000   0.2591   0.01714   0.00985  -0.1567   0.9397   0.0347
  -2.750   0.2885   0.01692   0.00957  -0.1572   0.9367   0.0405
  -2.500   0.3216   0.01635   0.00886  -0.1584   0.9347   0.0452
  -2.250   0.3558   0.01586   0.00833  -0.1598   0.9330   0.0504
  -2.000   0.3906   0.01546   0.00784  -0.1613   0.9315   0.0549
  -1.750   0.4258   0.01509   0.00742  -0.1630   0.9303   0.0588
  -1.500   0.4512   0.01490   0.00723  -0.1626   0.9255   0.0657
  -1.250   0.4817   0.01467   0.00699  -0.1632   0.9218   0.0754
  -1.000   0.5151   0.01439   0.00676  -0.1645   0.9196   0.0930
  -0.750   0.5495   0.01408   0.00665  -0.1660   0.9178   0.1512
  -0.500   0.5848   0.01378   0.00652  -0.1677   0.9163   0.2177
  -0.250   0.6117   0.01345   0.00667  -0.1679   0.9111   0.3744
   0.000   0.6430   0.01296   0.00678  -0.1688   0.9075   0.5881
   0.250   0.6638   0.01198   0.00650  -0.1663   0.9035   0.9681
   0.750   0.7272   0.01154   0.00596  -0.1672   0.8903   1.0000
   1.000   0.7584   0.01112   0.00549  -0.1673   0.8775   1.0000
   1.250   0.7920   0.01069   0.00501  -0.1678   0.8623   1.0000
   1.500   0.8255   0.01039   0.00469  -0.1685   0.8454   1.0000
   1.750   0.8598   0.01022   0.00450  -0.1695   0.8311   1.0000
   2.000   0.9020   0.00995   0.00422  -0.1721   0.8087   1.0000
   2.250   0.9506   0.00970   0.00383  -0.1760   0.7687   1.0000
   2.500   0.9900   0.00994   0.00360  -0.1778   0.6773   1.0000
   2.750   1.0041   0.01100   0.00390  -0.1746   0.5518   1.0000
   3.000   1.0221   0.01172   0.00431  -0.1726   0.5006   1.0000
   3.250   1.0419   0.01234   0.00471  -0.1710   0.4437   1.0000
   3.500   1.0546   0.01354   0.00525  -0.1682   0.3189   1.0000
   3.750   1.0741   0.01434   0.00581  -0.1668   0.2654   1.0000
   4.000   1.0939   0.01515   0.00635  -0.1655   0.2060   1.0000
   4.250   1.1110   0.01633   0.00703  -0.1638   0.1124   1.0000
   4.500   1.1309   0.01727   0.00773  -0.1625   0.0703   1.0000
   4.750   1.1532   0.01790   0.00833  -0.1615   0.0564   1.0000
   5.000   1.1756   0.01849   0.00896  -0.1605   0.0506   1.0000
   5.250   1.1980   0.01907   0.00961  -0.1595   0.0481   1.0000
   5.500   1.2203   0.01965   0.01032  -0.1584   0.0465   1.0000
   5.750   1.2417   0.02030   0.01110  -0.1572   0.0445   1.0000
   6.000   1.2618   0.02111   0.01197  -0.1559   0.0407   1.0000
   6.250   1.2799   0.02212   0.01310  -0.1542   0.0370   1.0000
   6.500   1.2999   0.02290   0.01401  -0.1529   0.0334   1.0000
   6.750   1.3170   0.02405   0.01522  -0.1511   0.0295   1.0000
   7.000   1.3356   0.02506   0.01636  -0.1496   0.0262   1.0000
   7.250   1.3551   0.02595   0.01742  -0.1480   0.0218   1.0000
   7.500   1.3730   0.02689   0.01842  -0.1464   0.0185   1.0000
   7.750   1.3900   0.02812   0.01976  -0.1446   0.0160   1.0000
   8.000   1.4074   0.02942   0.02128  -0.1428   0.0141   1.0000
   8.250   1.4242   0.03066   0.02265  -0.1410   0.0127   1.0000
   8.500   1.4397   0.03191   0.02401  -0.1391   0.0116   1.0000
   8.750   1.4552   0.03403   0.02632  -0.1373   0.0104   1.0000
   9.000   1.4718   0.03590   0.02846  -0.1355   0.0095   1.0000
   9.250   1.4868   0.03820   0.03104  -0.1336   0.0089   1.0000
   9.500   1.4989   0.04051   0.03364  -0.1313   0.0084   1.0000
   9.750   1.5075   0.04284   0.03624  -0.1285   0.0081   1.0000
  10.000   1.5126   0.04519   0.03885  -0.1255   0.0078   1.0000
  10.250   1.5140   0.04791   0.04186  -0.1221   0.0076   1.0000
  10.500   1.5104   0.05125   0.04552  -0.1184   0.0074   1.0000
  10.750   1.5009   0.05526   0.04989  -0.1144   0.0072   1.0000
  11.000   1.4898   0.05932   0.05433  -0.1106   0.0071   1.0000
  11.250   1.4752   0.06378   0.05917  -0.1072   0.0071   1.0000
  11.500   1.4571   0.06885   0.06466  -0.1044   0.0068   1.0000
  11.750   1.4377   0.07412   0.07020  -0.1026   0.0069   1.0000
  12.000   1.4159   0.08014   0.07653  -0.1019   0.0068   1.0000
  12.250   1.3931   0.08683   0.08349  -0.1026   0.0068   1.0000
  12.500   1.3715   0.09392   0.09080  -0.1048   0.0069   1.0000
  12.750   1.3522   0.10138   0.09844  -0.1083   0.0070   1.0000
  13.000   1.3312   0.11050   0.10775  -0.1139   0.0070   1.0000
  13.250   1.3116   0.12059   0.11799  -0.1207   0.0071   1.0000
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