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EPPLER 584 AIRFOIL (e584-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 584 AIRFOIL (e584-il)
Reynolds number: 100,000
Max Cl/Cd: 32.77 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e584-il-100000-n5.txt
Download as CSV file: xf-e584-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 584 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.1073   0.09337   0.08816  -0.1068   0.8802   0.0233
 -10.500  -0.0971   0.08931   0.08403  -0.1103   0.8685   0.0228
 -10.250  -0.0905   0.08490   0.07956  -0.1138   0.8580   0.0222
 -10.000  -0.0900   0.07976   0.07439  -0.1175   0.8479   0.0219
  -9.500  -0.1225   0.06308   0.05755  -0.1297   0.8290   0.0196
  -9.250  -0.1336   0.05933   0.05370  -0.1307   0.8195   0.0194
  -9.000  -0.1491   0.05545   0.04964  -0.1307   0.8120   0.0193
  -8.750  -0.1646   0.05263   0.04668  -0.1287   0.8040   0.0192
  -8.500  -0.1786   0.05009   0.04394  -0.1258   0.7977   0.0190
  -8.250  -0.1870   0.04735   0.04094  -0.1232   0.7925   0.0189
  -8.000  -0.1927   0.04480   0.03815  -0.1203   0.7867   0.0187
  -7.750  -0.1957   0.04193   0.03491  -0.1173   0.7817   0.0187
  -7.500  -0.1923   0.03921   0.03177  -0.1148   0.7779   0.0186
  -7.250  -0.1876   0.03693   0.02913  -0.1120   0.7729   0.0186
  -7.000  -0.1788   0.03463   0.02638  -0.1096   0.7685   0.0190
  -6.750  -0.1651   0.03238   0.02357  -0.1075   0.7650   0.0198
  -6.500  -0.1452   0.03125   0.02230  -0.1068   0.7621   0.0206
  -6.250  -0.1263   0.03012   0.02094  -0.1057   0.7589   0.0222
  -6.000  -0.1068   0.02870   0.01916  -0.1043   0.7550   0.0232
  -5.750  -0.0846   0.02742   0.01770  -0.1034   0.7514   0.0241
  -5.500  -0.0608   0.02637   0.01654  -0.1028   0.7483   0.0252
  -5.250  -0.0354   0.02531   0.01531  -0.1024   0.7456   0.0268
  -5.000  -0.0131   0.02449   0.01439  -0.1015   0.7428   0.0287
  -4.750   0.0051   0.02402   0.01386  -0.1000   0.7392   0.0326
  -4.500   0.0239   0.02348   0.01334  -0.0986   0.7357   0.0368
  -4.250   0.0440   0.02288   0.01269  -0.0973   0.7325   0.0428
  -4.000   0.0658   0.02229   0.01207  -0.0964   0.7298   0.0542
  -3.750   0.0884   0.02166   0.01153  -0.0956   0.7275   0.0764
  -3.500   0.1022   0.02132   0.01140  -0.0933   0.7235   0.1119
  -3.250   0.1182   0.02078   0.01127  -0.0916   0.7199   0.1851
  -3.000   0.1315   0.01993   0.01112  -0.0894   0.7166   0.3413
  -2.750   0.1773   0.02036   0.01314  -0.0881   0.7149   0.7382
  -2.500   0.1744   0.02049   0.01310  -0.0826   0.7122   0.7901
  -2.250   0.1799   0.02114   0.01367  -0.0779   0.7079   0.8202
  -2.000   0.1996   0.02179   0.01418  -0.0753   0.7042   0.8438
  -1.750   0.2323   0.02228   0.01449  -0.0752   0.7014   0.8640
  -1.500   0.2900   0.02282   0.01478  -0.0793   0.6995   0.8908
  -1.250   0.3738   0.02294   0.01460  -0.0894   0.6979   0.9100
  -1.000   0.3994   0.02301   0.01455  -0.0892   0.6950   0.9188
  -0.750   0.4301   0.02312   0.01457  -0.0904   0.6910   0.9241
  -0.500   0.4476   0.02322   0.01459  -0.0888   0.6875   0.9310
  -0.250   0.4814   0.02313   0.01437  -0.0903   0.6848   0.9341
   0.000   0.5159   0.02301   0.01411  -0.0920   0.6826   0.9370
   0.250   0.5337   0.02322   0.01429  -0.0907   0.6787   0.9417
   0.500   0.5477   0.02344   0.01448  -0.0886   0.6745   0.9463
   0.750   0.5778   0.02343   0.01439  -0.0895   0.6714   0.9485
   1.000   0.6089   0.02337   0.01423  -0.0906   0.6690   0.9507
   1.250   0.6353   0.02341   0.01420  -0.0907   0.6663   0.9532
   1.500   0.6377   0.02390   0.01475  -0.0866   0.6608   0.9581
   1.750   0.6638   0.02398   0.01479  -0.0868   0.6573   0.9599
   2.000   0.6955   0.02393   0.01468  -0.0880   0.6547   0.9614
   2.250   0.7240   0.02396   0.01466  -0.0885   0.6519   0.9630
   2.500   0.7273   0.02461   0.01540  -0.0849   0.6457   0.9668
   2.750   0.7482   0.02473   0.01551  -0.0840   0.6421   0.9690
   3.000   0.7755   0.02469   0.01542  -0.0841   0.6395   0.9702
   3.250   0.7823   0.02535   0.01617  -0.0813   0.6333   0.9733
   3.500   0.8006   0.02564   0.01649  -0.0802   0.6286   0.9754
   3.750   0.8290   0.02559   0.01643  -0.0806   0.6257   0.9763
   4.000   0.8244   0.02647   0.01741  -0.0758   0.6186   0.9805
   4.250   0.8386   0.02675   0.01772  -0.0739   0.6137   0.9828
   4.500   0.8707   0.02657   0.01754  -0.0748   0.6110   0.9833
   4.750   0.8542   0.02787   0.01897  -0.0686   0.6015   0.9881
   5.000   0.8827   0.02777   0.01890  -0.0690   0.5981   0.9895
   5.500   0.8818   0.02898   0.02025  -0.0611   0.5846   0.9973
   5.750   0.8831   0.02952   0.02084  -0.0575   0.5785   1.0000
   6.250   0.8067   0.03249   0.02386  -0.0390   0.5580   1.0000
   6.500   0.8248   0.03214   0.02353  -0.0373   0.5545   1.0000
   6.750   0.8539   0.03141   0.02285  -0.0369   0.5525   1.0000
   7.250   0.8527   0.03305   0.02456  -0.0304   0.5372   1.0000
   7.500   0.8871   0.03225   0.02379  -0.0308   0.5352   1.0000
   8.000   0.8664   0.03664   0.02831  -0.0252   0.5103   1.0000
   8.250   0.8969   0.03608   0.02782  -0.0254   0.5071   1.0000
   8.500   0.9337   0.03507   0.02688  -0.0259   0.5049   1.0000
   9.000   0.9658   0.03620   0.02815  -0.0246   0.4897   1.0000
   9.500   1.0018   0.03711   0.02922  -0.0237   0.4743   1.0000
  10.000   1.0417   0.03774   0.03001  -0.0230   0.4585   1.0000
  10.250   1.0436   0.03959   0.03195  -0.0218   0.4463   1.0000
  10.500   1.0755   0.03888   0.03132  -0.0220   0.4400   1.0000
  10.750   1.0866   0.03997   0.03249  -0.0213   0.4289   1.0000
  11.000   1.0979   0.04108   0.03369  -0.0206   0.4180   1.0000
  11.250   1.1347   0.03990   0.03255  -0.0209   0.4101   1.0000
  11.500   1.1379   0.04169   0.03443  -0.0199   0.3970   1.0000
  11.750   1.1476   0.04296   0.03577  -0.0192   0.3846   1.0000
  12.000   1.1630   0.04370   0.03657  -0.0187   0.3725   1.0000
  12.250   1.1798   0.04429   0.03720  -0.0182   0.3601   1.0000
  12.500   1.1947   0.04506   0.03799  -0.0176   0.3470   1.0000
  12.750   1.1999   0.04680   0.03979  -0.0169   0.3332   1.0000
  13.000   1.2062   0.04848   0.04152  -0.0162   0.3196   1.0000
  13.250   1.2126   0.05017   0.04326  -0.0156   0.3058   1.0000
  13.500   1.2187   0.05191   0.04503  -0.0150   0.2922   1.0000
  13.750   1.2241   0.05377   0.04691  -0.0145   0.2786   1.0000
  14.000   1.2288   0.05573   0.04889  -0.0140   0.2650   1.0000
  14.250   1.2321   0.05787   0.05104  -0.0135   0.2515   1.0000
  14.500   1.2346   0.06018   0.05336  -0.0132   0.2385   1.0000
  14.750   1.2346   0.06286   0.05611  -0.0130   0.2254   1.0000
  15.000   1.2348   0.06561   0.05891  -0.0128   0.2128   1.0000
  15.250   1.2346   0.06843   0.06177  -0.0128   0.2005   1.0000
  15.500   1.2340   0.07136   0.06473  -0.0129   0.1887   1.0000
  15.750   1.2324   0.07449   0.06786  -0.0130   0.1770   1.0000
  16.000   1.2302   0.07781   0.07124  -0.0134   0.1657   1.0000
  16.250   1.2278   0.08124   0.07474  -0.0139   0.1548   1.0000
  16.500   1.2248   0.08481   0.07836  -0.0145   0.1445   1.0000
  16.750   1.2211   0.08850   0.08205  -0.0152   0.1350   1.0000
  17.000   1.2175   0.09234   0.08599  -0.0161   0.1254   1.0000
  17.250   1.2140   0.09620   0.08991  -0.0170   0.1166   1.0000
  17.500   1.2088   0.10032   0.09402  -0.0182   0.1086   1.0000
  17.750   1.2051   0.10438   0.09820  -0.0195   0.1006   1.0000
  18.000   1.2007   0.10853   0.10240  -0.0209   0.0935   1.0000
  18.250   1.1958   0.11285   0.10678  -0.0224   0.0869   1.0000
  18.500   1.1924   0.11699   0.11100  -0.0240   0.0806   1.0000
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