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EPPLER 582 AIRFOIL (e582-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 582 AIRFOIL (e582-il)
Reynolds number: 100,000
Max Cl/Cd: 47.89 at α=9.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e582-il-100000.txt
Download as CSV file: xf-e582-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 582 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2750   0.10691   0.10268  -0.0636   0.9657   0.0914
  -8.500  -0.2761   0.10318   0.09897  -0.0696   0.9604   0.0957
  -8.250  -0.3027   0.10044   0.09631  -0.0752   0.9510   0.0970
  -8.000  -0.3322   0.09767   0.09351  -0.0798   0.9426   0.0974
  -7.750  -0.2626   0.09212   0.08797  -0.0762   0.9456   0.1046
  -7.500  -0.2772   0.09000   0.08589  -0.0758   0.9370   0.1065
  -7.250  -0.2944   0.08605   0.08192  -0.0818   0.9305   0.1101
  -7.000  -0.3274   0.08461   0.08044  -0.0801   0.9197   0.1113
  -6.750  -0.3511   0.08151   0.07714  -0.0812   0.9120   0.1132
  -6.500  -0.3284   0.07817   0.07400  -0.0784   0.9090   0.1165
  -6.250  -0.3234   0.07543   0.07121  -0.0785   0.9040   0.1225
  -6.000  -0.3373   0.07221   0.06773  -0.0795   0.8975   0.1295
  -5.750  -0.3318   0.07004   0.06566  -0.0767   0.8923   0.1329
  -5.500  -0.3265   0.06686   0.06220  -0.0784   0.8876   0.1453
  -5.250  -0.3060   0.06412   0.05946  -0.0788   0.8842   0.1541
  -5.000  -0.3167   0.06243   0.05766  -0.0754   0.8772   0.1622
  -4.750  -0.3014   0.05984   0.05496  -0.0758   0.8733   0.1777
  -4.500  -0.2746   0.05686   0.05190  -0.0774   0.8705   0.1968
  -4.250  -0.2315   0.04584   0.03820  -0.0776   0.8663   0.0575
  -4.000  -0.2126   0.04287   0.03510  -0.0770   0.8620   0.0550
  -3.750  -0.1817   0.04040   0.03220  -0.0776   0.8587   0.0524
  -3.500  -0.1432   0.03848   0.02984  -0.0791   0.8559   0.0530
  -3.250  -0.1261   0.03779   0.02889  -0.0774   0.8508   0.0549
  -3.000  -0.1045   0.03685   0.02766  -0.0761   0.8460   0.0580
  -2.750  -0.0729   0.03549   0.02634  -0.0767   0.8426   0.0622
  -2.500  -0.0334   0.03435   0.02522  -0.0784   0.8398   0.0758
  -2.250  -0.0296   0.03433   0.02518  -0.0748   0.8331   0.0843
  -2.000  -0.0044   0.03318   0.02442  -0.0747   0.8288   0.1382
  -1.750  -0.0061   0.03103   0.02534  -0.0670   0.8257   0.7710
  -1.500  -0.0205   0.03211   0.02641  -0.0575   0.8190   0.8399
  -1.250   0.2631   0.03292   0.02616  -0.0955   0.8262   1.0000
  -1.000   0.2511   0.03368   0.02688  -0.0900   0.8181   1.0000
  -0.750   0.2656   0.03395   0.02701  -0.0885   0.8124   1.0000
  -0.500   0.3035   0.03389   0.02676  -0.0907   0.8093   1.0000
  -0.250   0.2726   0.03494   0.02782  -0.0822   0.7988   1.0000
   0.000   0.3047   0.03498   0.02771  -0.0833   0.7949   1.0000
   0.250   0.2845   0.03588   0.02858  -0.0765   0.7857   1.0000
   0.500   0.3082   0.03604   0.02862  -0.0763   0.7806   1.0000
   0.750   0.3483   0.03603   0.02848  -0.0784   0.7776   1.0000
   1.000   0.3157   0.03701   0.02947  -0.0699   0.7664   1.0000
   1.250   0.3566   0.03695   0.02928  -0.0720   0.7631   1.0000
   1.500   0.3260   0.03789   0.03023  -0.0639   0.7519   1.0000
   1.750   0.3651   0.03782   0.03005  -0.0656   0.7482   1.0000
   2.000   0.3395   0.03870   0.03094  -0.0583   0.7373   1.0000
   2.250   0.3763   0.03865   0.03080  -0.0596   0.7333   1.0000
   2.500   0.3622   0.03954   0.03168  -0.0544   0.7226   1.0000
   2.750   0.3996   0.03953   0.03159  -0.0558   0.7184   1.0000
   3.000   0.3998   0.04052   0.03257  -0.0531   0.7081   1.0000
   3.250   0.4376   0.04053   0.03252  -0.0546   0.7035   1.0000
   3.500   0.4452   0.04155   0.03353  -0.0530   0.6934   1.0000
   3.750   0.4825   0.04154   0.03349  -0.0545   0.6886   1.0000
   4.000   0.4944   0.04253   0.03449  -0.0535   0.6786   1.0000
   4.250   0.5320   0.04246   0.03439  -0.0549   0.6736   1.0000
   4.500   0.5801   0.04190   0.03384  -0.0572   0.6710   1.0000
   4.750   0.5843   0.04323   0.03519  -0.0556   0.6585   1.0000
   5.000   0.6325   0.04252   0.03450  -0.0577   0.6561   1.0000
   5.250   0.6388   0.04382   0.03582  -0.0563   0.6435   1.0000
   5.500   0.6881   0.04286   0.03492  -0.0584   0.6413   1.0000
   5.750   0.6952   0.04418   0.03627  -0.0571   0.6285   1.0000
   6.000   0.7449   0.04300   0.03515  -0.0590   0.6265   1.0000
   6.250   0.7531   0.04427   0.03649  -0.0578   0.6136   1.0000
   6.500   0.8038   0.04278   0.03508  -0.0596   0.6117   1.0000
   6.750   0.8128   0.04400   0.03636  -0.0584   0.5987   1.0000
   7.000   0.8654   0.04208   0.03455  -0.0601   0.5971   1.0000
   7.250   0.8750   0.04326   0.03580  -0.0589   0.5841   1.0000
   7.500   0.8903   0.04403   0.03665  -0.0581   0.5725   1.0000
   7.750   0.9420   0.04169   0.03446  -0.0592   0.5701   1.0000
   8.000   1.0009   0.03857   0.03149  -0.0608   0.5691   1.0000
   8.250   1.0704   0.03495   0.02805  -0.0636   0.5682   1.0000
   8.500   1.0884   0.03507   0.02828  -0.0624   0.5560   1.0000
   8.750   1.1790   0.03056   0.02398  -0.0678   0.5530   1.0000
   9.000   1.2064   0.03000   0.02354  -0.0673   0.5397   1.0000
   9.250   1.2413   0.02909   0.02274  -0.0677   0.5256   1.0000
   9.500   1.2780   0.02814   0.02187  -0.0682   0.5096   1.0000
   9.750   1.3127   0.02741   0.02116  -0.0686   0.4912   1.0000
  10.000   1.3189   0.02800   0.02181  -0.0657   0.4717   1.0000
  10.250   1.3361   0.02819   0.02202  -0.0642   0.4507   1.0000
  10.500   1.3507   0.02860   0.02241  -0.0624   0.4290   1.0000
  10.750   1.3564   0.02949   0.02329  -0.0598   0.4070   1.0000
  11.000   1.3663   0.03030   0.02402  -0.0578   0.3847   1.0000
  11.250   1.3670   0.03162   0.02533  -0.0550   0.3629   1.0000
  11.500   1.3731   0.03278   0.02638  -0.0528   0.3409   1.0000
  11.750   1.3706   0.03448   0.02811  -0.0501   0.3200   1.0000
  12.000   1.3709   0.03612   0.02968  -0.0478   0.2993   1.0000
  12.250   1.3698   0.03796   0.03147  -0.0456   0.2793   1.0000
  12.500   1.3664   0.04004   0.03355  -0.0434   0.2599   1.0000
  12.750   1.3638   0.04218   0.03563  -0.0415   0.2412   1.0000
  13.000   1.3621   0.04436   0.03770  -0.0398   0.2230   1.0000
  13.250   1.3567   0.04695   0.04033  -0.0381   0.2056   1.0000
  13.500   1.3518   0.04964   0.04302  -0.0367   0.1886   1.0000
  13.750   1.3467   0.05248   0.04584  -0.0355   0.1724   1.0000
  14.000   1.3418   0.05544   0.04876  -0.0344   0.1571   1.0000
  14.250   1.3372   0.05853   0.05184  -0.0336   0.1425   1.0000
  14.500   1.3328   0.06172   0.05501  -0.0328   0.1288   1.0000
  14.750   1.3284   0.06505   0.05833  -0.0323   0.1161   1.0000
  15.000   1.3252   0.06840   0.06169  -0.0318   0.1044   1.0000
  15.250   1.3232   0.07171   0.06501  -0.0315   0.0941   1.0000
  15.500   1.3230   0.07487   0.06812  -0.0312   0.0847   1.0000
  15.750   1.3208   0.07831   0.07160  -0.0313   0.0768   1.0000
  16.000   1.3196   0.08190   0.07534  -0.0312   0.0697   1.0000
  16.250   1.3241   0.08469   0.07803  -0.0311   0.0627   1.0000
  16.500   1.3184   0.08892   0.08255  -0.0316   0.0582   1.0000
  16.750   1.3246   0.09167   0.08520  -0.0315   0.0524   1.0000
  17.000   1.3160   0.09644   0.09030  -0.0325   0.0493   1.0000
  17.250   1.3159   0.09996   0.09390  -0.0332   0.0457   1.0000
  17.500   1.3144   0.10402   0.09808  -0.0339   0.0425   1.0000
  17.750   1.3029   0.10945   0.10382  -0.0357   0.0406   1.0000
  18.000   1.2944   0.11454   0.10913  -0.0375   0.0388   1.0000
  18.250   1.3036   0.11700   0.11143  -0.0377   0.0354   1.0000
  18.500   1.2867   0.12351   0.11827  -0.0408   0.0349   1.0000
  18.750   1.2687   0.13048   0.12554  -0.0444   0.0345   1.0000
  19.000   1.2506   0.13782   0.13316  -0.0486   0.0344   1.0000
  19.250   1.2318   0.14568   0.14126  -0.0532   0.0344   1.0000
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