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E591 (e591-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: E591 (e591-il)
Reynolds number: 1,000,000
Max Cl/Cd: 129.91 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e591-il-1000000.txt
Download as CSV file: xf-e591-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.3274   0.05955   0.05726  -0.1114   0.9774   0.0132
 -11.250  -0.3589   0.04595   0.04337  -0.1284   0.9734   0.0130
 -11.000  -0.3718   0.03954   0.03681  -0.1351   0.9638   0.0130
 -10.750  -0.3816   0.03369   0.03078  -0.1416   0.9527   0.0130
 -10.500  -0.3703   0.02780   0.02466  -0.1519   0.9430   0.0131
 -10.250  -0.3347   0.02403   0.02065  -0.1624   0.9384   0.0131
 -10.000  -0.3034   0.02202   0.01846  -0.1670   0.9323   0.0132
  -9.750  -0.2701   0.01883   0.01498  -0.1731   0.9260   0.0135
  -9.500  -0.2264   0.01719   0.01321  -0.1785   0.9227   0.0138
  -9.250  -0.1888   0.01632   0.01228  -0.1816   0.9150   0.0141
  -9.000  -0.1413   0.01556   0.01143  -0.1865   0.9093   0.0145
  -8.750  -0.0985   0.01483   0.01060  -0.1903   0.9006   0.0150
  -8.250  -0.0252   0.01353   0.00903  -0.1950   0.8760   0.0157
  -8.000   0.0055   0.01303   0.00841  -0.1960   0.8619   0.0159
  -7.750   0.0349   0.01272   0.00797  -0.1964   0.8476   0.0161
  -7.500   0.0629   0.01187   0.00699  -0.1972   0.8331   0.0167
  -7.250   0.0906   0.01151   0.00654  -0.1974   0.8188   0.0171
  -7.000   0.1180   0.01123   0.00619  -0.1974   0.8051   0.0175
  -6.750   0.1453   0.01097   0.00583  -0.1973   0.7914   0.0180
  -6.500   0.1725   0.01074   0.00550  -0.1972   0.7776   0.0186
  -6.250   0.2000   0.01055   0.00521  -0.1971   0.7643   0.0191
  -6.000   0.2283   0.01015   0.00473  -0.1974   0.7513   0.0200
  -5.750   0.2556   0.00998   0.00448  -0.1972   0.7381   0.0208
  -5.500   0.2834   0.00984   0.00427  -0.1971   0.7251   0.0218
  -5.250   0.3115   0.00967   0.00401  -0.1971   0.7127   0.0229
  -5.000   0.3391   0.00952   0.00380  -0.1970   0.6999   0.0245
  -4.750   0.3673   0.00943   0.00364  -0.1969   0.6876   0.0261
  -4.500   0.3960   0.00923   0.00338  -0.1970   0.6757   0.0284
  -4.000   0.4526   0.00902   0.00304  -0.1970   0.6518   0.0341
  -3.750   0.4808   0.00892   0.00289  -0.1970   0.6401   0.0383
  -3.500   0.5095   0.00883   0.00276  -0.1970   0.6281   0.0442
  -3.250   0.5385   0.00869   0.00264  -0.1972   0.6173   0.0588
  -3.000   0.5678   0.00850   0.00252  -0.1976   0.6055   0.0955
  -2.750   0.5980   0.00827   0.00242  -0.1982   0.5948   0.1477
  -2.500   0.6267   0.00817   0.00239  -0.1984   0.5836   0.1928
  -2.250   0.6558   0.00811   0.00239  -0.1986   0.5733   0.2270
  -2.000   0.6837   0.00813   0.00241  -0.1985   0.5628   0.2528
  -1.750   0.7121   0.00815   0.00243  -0.1984   0.5527   0.2706
  -1.500   0.7398   0.00821   0.00246  -0.1983   0.5430   0.2862
  -1.250   0.7677   0.00827   0.00249  -0.1981   0.5331   0.3007
  -1.000   0.7952   0.00835   0.00254  -0.1979   0.5237   0.3153
  -0.750   0.8233   0.00840   0.00259  -0.1978   0.5146   0.3297
  -0.500   0.8506   0.00850   0.00265  -0.1975   0.5055   0.3429
  -0.250   0.8783   0.00858   0.00271  -0.1974   0.4967   0.3571
   0.000   0.9054   0.00868   0.00278  -0.1971   0.4879   0.3683
   0.250   0.9333   0.00875   0.00283  -0.1969   0.4802   0.3780
   0.500   0.9601   0.00887   0.00291  -0.1966   0.4712   0.3883
   0.750   0.9877   0.00895   0.00298  -0.1964   0.4641   0.3988
   1.000   1.0149   0.00905   0.00307  -0.1962   0.4561   0.4103
   1.250   1.0417   0.00918   0.00316  -0.1959   0.4487   0.4209
   1.500   1.0691   0.00926   0.00325  -0.1957   0.4414   0.4341
   1.750   1.0952   0.00941   0.00336  -0.1952   0.4336   0.4464
   2.000   1.1226   0.00949   0.00346  -0.1951   0.4274   0.4605
   2.250   1.1492   0.00961   0.00358  -0.1947   0.4202   0.4754
   2.500   1.1751   0.00976   0.00371  -0.1943   0.4131   0.4903
   3.000   1.2281   0.01000   0.00397  -0.1936   0.4003   0.5248
   3.250   1.2540   0.01014   0.00412  -0.1932   0.3938   0.5430
   3.500   1.2804   0.01025   0.00426  -0.1929   0.3879   0.5626
   3.750   1.3054   0.01042   0.00443  -0.1923   0.3809   0.5838
   4.000   1.3308   0.01055   0.00459  -0.1918   0.3749   0.6056
   4.250   1.3560   0.01067   0.00475  -0.1912   0.3689   0.6286
   4.500   1.3796   0.01086   0.00495  -0.1904   0.3621   0.6551
   4.750   1.4044   0.01098   0.00512  -0.1898   0.3564   0.6837
   5.000   1.4287   0.01113   0.00532  -0.1891   0.3503   0.7141
   5.250   1.4514   0.01134   0.00556  -0.1881   0.3434   0.7507
   5.500   1.4754   0.01144   0.00577  -0.1873   0.3382   0.7978
   5.750   1.4961   0.01154   0.00599  -0.1859   0.3322   0.8658
   6.000   1.5096   0.01162   0.00616  -0.1829   0.3262   1.0000
   6.250   1.5335   0.01182   0.00635  -0.1821   0.3212   1.0000
   6.500   1.5562   0.01206   0.00657  -0.1812   0.3152   1.0000
   6.750   1.5771   0.01239   0.00685  -0.1800   0.3087   1.0000
   7.000   1.6002   0.01261   0.00707  -0.1792   0.3044   1.0000
   7.250   1.6218   0.01288   0.00733  -0.1781   0.2987   1.0000
   7.500   1.6414   0.01326   0.00766  -0.1767   0.2922   1.0000
   7.750   1.6637   0.01350   0.00792  -0.1757   0.2880   1.0000
   8.000   1.6848   0.01381   0.00821  -0.1746   0.2827   1.0000
   8.250   1.7033   0.01422   0.00858  -0.1731   0.2766   1.0000
   8.500   1.7239   0.01453   0.00891  -0.1719   0.2722   1.0000
   8.750   1.7441   0.01486   0.00925  -0.1707   0.2674   1.0000
   9.000   1.7621   0.01531   0.00967  -0.1692   0.2618   1.0000
   9.250   1.7805   0.01572   0.01008  -0.1677   0.2571   1.0000
   9.500   1.7998   0.01610   0.01047  -0.1664   0.2525   1.0000
   9.750   1.8169   0.01659   0.01095  -0.1648   0.2474   1.0000
  10.000   1.8328   0.01714   0.01149  -0.1630   0.2423   1.0000
  10.250   1.8514   0.01756   0.01194  -0.1617   0.2382   1.0000
  10.500   1.8673   0.01812   0.01250  -0.1601   0.2334   1.0000
  10.750   1.8804   0.01884   0.01320  -0.1580   0.2277   1.0000
  11.000   1.8980   0.01933   0.01373  -0.1567   0.2243   1.0000
  11.250   1.9131   0.01996   0.01438  -0.1550   0.2199   1.0000
  11.500   1.9253   0.02078   0.01519  -0.1531   0.2149   1.0000
  11.750   1.9394   0.02151   0.01594  -0.1514   0.2109   1.0000
  12.000   1.9538   0.02222   0.01669  -0.1498   0.2070   1.0000
  12.250   1.9655   0.02313   0.01760  -0.1480   0.2026   1.0000
  12.500   1.9745   0.02424   0.01871  -0.1459   0.1977   1.0000
  12.750   1.9889   0.02503   0.01955  -0.1445   0.1945   1.0000
  13.000   1.9997   0.02607   0.02062  -0.1428   0.1905   1.0000
  13.250   2.0071   0.02739   0.02195  -0.1409   0.1860   1.0000
  13.500   2.0173   0.02856   0.02316  -0.1393   0.1824   1.0000
  13.750   2.0278   0.02974   0.02438  -0.1378   0.1789   1.0000
  14.000   2.0352   0.03119   0.02586  -0.1362   0.1750   1.0000
  14.250   2.0389   0.03301   0.02769  -0.1344   0.1705   1.0000
  14.500   2.0489   0.03435   0.02910  -0.1332   0.1677   1.0000
  14.750   2.0562   0.03597   0.03076  -0.1319   0.1642   1.0000
  15.000   2.0598   0.03799   0.03280  -0.1304   0.1603   1.0000
  15.250   2.0622   0.04018   0.03503  -0.1291   0.1565   1.0000
  15.500   2.0693   0.04198   0.03690  -0.1281   0.1537   1.0000
  15.750   2.0728   0.04420   0.03917  -0.1271   0.1503   1.0000
  16.000   2.0720   0.04694   0.04194  -0.1260   0.1466   1.0000
  16.250   2.0735   0.04952   0.04458  -0.1252   0.1434   1.0000
  16.500   2.0773   0.05190   0.04703  -0.1245   0.1405   1.0000
  16.750   2.0764   0.05488   0.05006  -0.1239   0.1372   1.0000
  17.000   2.0710   0.05849   0.05371  -0.1234   0.1337   1.0000
  17.250   2.0707   0.06158   0.05687  -0.1230   0.1309   1.0000
  17.500   2.0713   0.06460   0.05997  -0.1228   0.1282   1.0000
  17.750   2.0669   0.06833   0.06376  -0.1227   0.1251   1.0000
  18.000   2.0577   0.07281   0.06828  -0.1229   0.1219   1.0000
  18.250   2.0542   0.07658   0.07215  -0.1231   0.1196   1.0000
  18.500   2.0512   0.08036   0.07600  -0.1234   0.1170   1.0000
  18.750   2.0439   0.08479   0.08050  -0.1239   0.1142   1.0000
  19.000   2.0318   0.08998   0.08576  -0.1248   0.1113   1.0000
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