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E591 (e591-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: E591 (e591-il)
Reynolds number: 200,000
Max Cl/Cd: 76.45 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e591-il-200000-n5.txt
Download as CSV file: xf-e591-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E591                                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.0573   0.09133   0.08759  -0.0866   0.9400   0.0217
  -9.000  -0.0515   0.08656   0.08283  -0.0899   0.9333   0.0215
  -8.500  -0.2088   0.04044   0.03601  -0.1302   0.8943   0.0198
  -8.250  -0.1847   0.03398   0.02909  -0.1441   0.8842   0.0201
  -8.000  -0.1536   0.03040   0.02511  -0.1510   0.8765   0.0205
  -7.750  -0.1142   0.02752   0.02186  -0.1573   0.8712   0.0211
  -7.500  -0.0826   0.02536   0.01932  -0.1607   0.8618   0.0220
  -7.250  -0.0381   0.02349   0.01713  -0.1658   0.8562   0.0229
  -7.000  -0.0024   0.02245   0.01600  -0.1683   0.8473   0.0238
  -6.750   0.0386   0.02117   0.01451  -0.1718   0.8391   0.0247
  -6.500   0.0748   0.02002   0.01314  -0.1741   0.8295   0.0256
  -6.250   0.1129   0.01901   0.01196  -0.1767   0.8196   0.0265
  -6.000   0.1461   0.01829   0.01118  -0.1782   0.8085   0.0275
  -5.500   0.2138   0.01700   0.00965  -0.1811   0.7857   0.0306
  -5.250   0.2468   0.01650   0.00907  -0.1825   0.7745   0.0327
  -5.000   0.2788   0.01601   0.00846  -0.1835   0.7623   0.0350
  -4.750   0.3096   0.01558   0.00795  -0.1843   0.7504   0.0373
  -4.500   0.3420   0.01518   0.00743  -0.1853   0.7389   0.0402
  -4.250   0.3717   0.01487   0.00704  -0.1858   0.7264   0.0446
  -4.000   0.4022   0.01457   0.00665  -0.1864   0.7148   0.0502
  -3.750   0.4328   0.01429   0.00630  -0.1871   0.7030   0.0583
  -3.500   0.4626   0.01400   0.00599  -0.1876   0.6911   0.0726
  -3.250   0.4934   0.01366   0.00568  -0.1884   0.6798   0.1037
  -3.000   0.5235   0.01333   0.00549  -0.1891   0.6678   0.1591
  -2.750   0.5528   0.01319   0.00541  -0.1894   0.6567   0.2070
  -2.500   0.5811   0.01317   0.00537  -0.1895   0.6451   0.2411
  -2.250   0.6091   0.01318   0.00537  -0.1894   0.6340   0.2690
  -1.750   0.6644   0.01332   0.00542  -0.1890   0.6123   0.3207
  -1.500   0.6917   0.01343   0.00542  -0.1887   0.6021   0.3376
  -1.250   0.7189   0.01350   0.00547  -0.1884   0.5914   0.3536
  -1.000   0.7459   0.01360   0.00550  -0.1881   0.5816   0.3666
  -0.750   0.7728   0.01370   0.00551  -0.1878   0.5714   0.3785
  -0.500   0.7997   0.01380   0.00556  -0.1874   0.5620   0.3891
  -0.250   0.8264   0.01391   0.00560  -0.1871   0.5522   0.4007
   0.000   0.8529   0.01403   0.00568  -0.1867   0.5433   0.4114
   0.250   0.8795   0.01415   0.00575  -0.1863   0.5339   0.4232
   0.500   0.9057   0.01429   0.00584  -0.1859   0.5254   0.4348
   0.750   0.9321   0.01441   0.00595  -0.1855   0.5164   0.4471
   1.000   0.9580   0.01458   0.00606  -0.1850   0.5083   0.4602
   1.250   0.9841   0.01471   0.00620  -0.1846   0.4998   0.4733
   1.500   1.0096   0.01488   0.00633  -0.1840   0.4916   0.4877
   1.750   1.0354   0.01504   0.00649  -0.1835   0.4840   0.5027
   2.000   1.0608   0.01521   0.00666  -0.1830   0.4759   0.5182
   2.250   1.0858   0.01541   0.00683  -0.1824   0.4687   0.5349
   2.500   1.1113   0.01557   0.00703  -0.1819   0.4610   0.5524
   2.750   1.1359   0.01578   0.00723  -0.1812   0.4537   0.5714
   3.000   1.1607   0.01597   0.00745  -0.1806   0.4467   0.5918
   3.250   1.1851   0.01617   0.00768  -0.1799   0.4393   0.6133
   3.750   1.2329   0.01659   0.00818  -0.1783   0.4258   0.6630
   4.000   1.2558   0.01681   0.00844  -0.1774   0.4188   0.6909
   4.250   1.2779   0.01705   0.00870  -0.1762   0.4127   0.7228
   4.500   1.2994   0.01722   0.00897  -0.1749   0.4061   0.7610
   4.750   1.3172   0.01740   0.00921  -0.1729   0.3997   0.8091
   5.000   1.3252   0.01738   0.00931  -0.1687   0.3946   0.9360
   5.250   1.3479   0.01763   0.00957  -0.1678   0.3881   1.0000
   5.500   1.3695   0.01800   0.00989  -0.1668   0.3817   1.0000
   5.750   1.3908   0.01838   0.01022  -0.1657   0.3760   1.0000
   6.000   1.4125   0.01872   0.01056  -0.1647   0.3695   1.0000
   6.250   1.4327   0.01912   0.01093  -0.1635   0.3634   1.0000
   6.500   1.4527   0.01955   0.01132  -0.1622   0.3578   1.0000
   6.750   1.4730   0.01994   0.01173  -0.1611   0.3516   1.0000
   7.000   1.4918   0.02040   0.01216  -0.1597   0.3457   1.0000
   7.250   1.5105   0.02087   0.01263  -0.1583   0.3404   1.0000
   7.500   1.5295   0.02132   0.01311  -0.1570   0.3343   1.0000
   7.750   1.5468   0.02185   0.01363  -0.1554   0.3286   1.0000
   8.000   1.5639   0.02241   0.01417  -0.1539   0.3234   1.0000
   8.250   1.5817   0.02294   0.01475  -0.1525   0.3177   1.0000
   8.500   1.5975   0.02355   0.01537  -0.1508   0.3122   1.0000
   8.750   1.6126   0.02423   0.01603  -0.1491   0.3072   1.0000
   9.000   1.6293   0.02484   0.01671  -0.1477   0.3018   1.0000
   9.250   1.6438   0.02556   0.01745  -0.1460   0.2964   1.0000
   9.500   1.6565   0.02639   0.01826  -0.1441   0.2916   1.0000
   9.750   1.6721   0.02711   0.01906  -0.1427   0.2866   1.0000
  10.000   1.6855   0.02794   0.01994  -0.1410   0.2814   1.0000
  10.250   1.6969   0.02891   0.02091  -0.1392   0.2767   1.0000
  10.500   1.7097   0.02985   0.02190  -0.1376   0.2720   1.0000
  10.750   1.7221   0.03082   0.02295  -0.1361   0.2670   1.0000
  11.000   1.7323   0.03195   0.02411  -0.1344   0.2623   1.0000
  11.250   1.7417   0.03317   0.02535  -0.1327   0.2581   1.0000
  11.500   1.7533   0.03430   0.02658  -0.1313   0.2533   1.0000
  11.750   1.7624   0.03561   0.02796  -0.1298   0.2486   1.0000
  12.000   1.7695   0.03711   0.02947  -0.1281   0.2444   1.0000
  12.250   1.7786   0.03852   0.03097  -0.1268   0.2401   1.0000
  12.500   1.7869   0.04004   0.03258  -0.1255   0.2355   1.0000
  12.750   1.7928   0.04177   0.03436  -0.1241   0.2312   1.0000
  13.000   1.7976   0.04366   0.03627  -0.1228   0.2274   1.0000
  13.250   1.8054   0.04538   0.03812  -0.1218   0.2230   1.0000
  13.500   1.8106   0.04737   0.04020  -0.1207   0.2187   1.0000
  13.750   1.8137   0.04959   0.04246  -0.1197   0.2147   1.0000
  14.000   1.8177   0.05181   0.04475  -0.1188   0.2110   1.0000
  14.250   1.8224   0.05405   0.04712  -0.1181   0.2068   1.0000
  14.500   1.8247   0.05657   0.04972  -0.1174   0.2027   1.0000
  14.750   1.8256   0.05930   0.05248  -0.1168   0.1991   1.0000
  15.000   1.8282   0.06193   0.05523  -0.1163   0.1955   1.0000
  15.250   1.8299   0.06474   0.05816  -0.1160   0.1915   1.0000
  15.500   1.8297   0.06782   0.06132  -0.1158   0.1877   1.0000
  15.750   1.8287   0.07103   0.06456  -0.1156   0.1844   1.0000
  16.000   1.8294   0.07417   0.06784  -0.1157   0.1808   1.0000
  16.250   1.8285   0.07755   0.07136  -0.1158   0.1770   1.0000
  16.500   1.8261   0.08116   0.07504  -0.1161   0.1734   1.0000
  16.750   1.8240   0.08474   0.07863  -0.1164   0.1703   1.0000
  17.000   1.8223   0.08845   0.08252  -0.1169   0.1668   1.0000
  17.250   1.8192   0.09236   0.08656  -0.1176   0.1632   1.0000
  17.500   1.8157   0.09633   0.09060  -0.1184   0.1598   1.0000
  17.750   1.8137   0.10002   0.09430  -0.1191   0.1568   1.0000
  18.000   1.8095   0.10427   0.09875  -0.1202   0.1534   1.0000
  18.250   1.8046   0.10861   0.10321  -0.1214   0.1500   1.0000
  18.500   1.8011   0.11269   0.10735  -0.1226   0.1468   1.0000
  18.750   1.7996   0.11639   0.11107  -0.1237   0.1439   1.0000
  19.000   1.7932   0.12110   0.11596  -0.1254   0.1406   1.0000
  19.250   1.7879   0.12555   0.12053  -0.1271   0.1372   1.0000
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