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EPPLER 580 AIRFOIL (e580-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 580 AIRFOIL (e580-il)
Reynolds number: 50,000
Max Cl/Cd: 24.39 at α=9°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e580-il-50000-n5.txt
Download as CSV file: xf-e580-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 580 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3603   0.10916   0.10253  -0.0506   1.0000   0.0538
  -9.750  -0.3710   0.10557   0.09904  -0.0506   1.0000   0.0534
  -9.500  -0.3836   0.10181   0.09538  -0.0505   1.0000   0.0529
  -9.250  -0.3993   0.09762   0.09129  -0.0508   1.0000   0.0521
  -8.750  -0.5120   0.08296   0.07662  -0.0565   0.9987   0.0468
  -8.500  -0.5172   0.07761   0.07111  -0.0627   0.9891   0.0466
  -8.250  -0.5171   0.07229   0.06554  -0.0687   0.9793   0.0465
  -8.000  -0.5132   0.06712   0.05999  -0.0740   0.9696   0.0467
  -7.750  -0.5034   0.06261   0.05519  -0.0777   0.9607   0.0473
  -7.500  -0.4887   0.05921   0.05159  -0.0798   0.9524   0.0480
  -7.250  -0.4665   0.05567   0.04776  -0.0831   0.9460   0.0489
  -7.000  -0.4499   0.05245   0.04415  -0.0847   0.9371   0.0492
  -6.750  -0.4222   0.04911   0.04034  -0.0876   0.9315   0.0495
  -6.500  -0.4007   0.04659   0.03746  -0.0884   0.9232   0.0499
  -6.250  -0.3680   0.04412   0.03462  -0.0906   0.9183   0.0507
  -6.000  -0.3458   0.04234   0.03257  -0.0904   0.9100   0.0516
  -5.750  -0.3129   0.04061   0.03057  -0.0915   0.9049   0.0531
  -5.500  -0.2894   0.03947   0.02918  -0.0908   0.8971   0.0555
  -5.250  -0.2593   0.03835   0.02788  -0.0907   0.8914   0.0587
  -5.000  -0.2356   0.03747   0.02702  -0.0898   0.8844   0.0616
  -4.500  -0.1813   0.03583   0.02512  -0.0891   0.8719   0.0687
  -4.250  -0.1596   0.03499   0.02427  -0.0888   0.8635   0.0734
  -4.000  -0.1243   0.03375   0.02302  -0.0912   0.8588   0.0866
  -3.750  -0.1016   0.03261   0.02200  -0.0922   0.8498   0.1084
  -3.500  -0.0712   0.03004   0.02167  -0.0951   0.8451   0.3901
  -3.250  -0.0518   0.03185   0.02347  -0.0917   0.8358   0.5546
  -3.000  -0.0395   0.03387   0.02548  -0.0845   0.8293   0.6125
  -2.750  -0.0340   0.03502   0.02658  -0.0781   0.8197   0.6430
  -2.500  -0.0143   0.03547   0.02684  -0.0743   0.8141   0.6643
  -2.250   0.0060   0.03548   0.02663  -0.0735   0.8056   0.6753
  -2.000   0.0362   0.03522   0.02612  -0.0741   0.7999   0.6824
  -1.750   0.0675   0.03497   0.02561  -0.0757   0.7935   0.6894
  -1.500   0.0910   0.03488   0.02534  -0.0753   0.7860   0.6942
  -1.250   0.1300   0.03445   0.02467  -0.0777   0.7821   0.6998
  -1.000   0.1511   0.03458   0.02464  -0.0780   0.7726   0.7050
  -0.750   0.1840   0.03427   0.02416  -0.0789   0.7679   0.7090
  -0.500   0.2062   0.03439   0.02415  -0.0789   0.7596   0.7135
  -0.250   0.2418   0.03419   0.02377  -0.0811   0.7539   0.7184
   0.000   0.2808   0.03380   0.02323  -0.0831   0.7505   0.7222
   0.250   0.2942   0.03424   0.02362  -0.0817   0.7400   0.7262
   0.500   0.3338   0.03391   0.02315  -0.0840   0.7361   0.7305
   0.750   0.3552   0.03436   0.02352  -0.0845   0.7266   0.7351
   1.000   0.3885   0.03413   0.02322  -0.0854   0.7217   0.7386
   1.250   0.4099   0.03447   0.02351  -0.0852   0.7136   0.7426
   1.500   0.4422   0.03448   0.02344  -0.0865   0.7074   0.7470
   1.750   0.4858   0.03410   0.02298  -0.0893   0.7040   0.7513
   2.000   0.4952   0.03489   0.02378  -0.0874   0.6932   0.7552
   2.250   0.5345   0.03455   0.02339  -0.0893   0.6893   0.7595
   2.500   0.5499   0.03537   0.02422  -0.0887   0.6791   0.7641
   2.750   0.5869   0.03512   0.02394  -0.0902   0.6746   0.7683
   3.000   0.6012   0.03586   0.02472  -0.0890   0.6650   0.7728
   3.250   0.6364   0.03574   0.02460  -0.0904   0.6597   0.7778
   3.750   0.6851   0.03644   0.02535  -0.0904   0.6448   0.7873
   4.000   0.7234   0.03614   0.02507  -0.0920   0.6404   0.7927
   4.250   0.7345   0.03723   0.02623  -0.0907   0.6297   0.7983
   4.500   0.7751   0.03665   0.02569  -0.0922   0.6261   0.8037
   4.750   0.7807   0.03805   0.02717  -0.0903   0.6144   0.8098
   5.000   0.8220   0.03745   0.02664  -0.0919   0.6107   0.8159
   5.250   0.8248   0.03895   0.02825  -0.0896   0.5989   0.8226
   5.500   0.8672   0.03827   0.02763  -0.0912   0.5951   0.8300
   5.750   0.8677   0.03990   0.02938  -0.0887   0.5831   0.8378
   6.000   0.9106   0.03909   0.02867  -0.0902   0.5794   0.8462
   6.250   0.9093   0.04088   0.03059  -0.0876   0.5671   0.8557
   6.500   0.9522   0.03987   0.02969  -0.0888   0.5635   0.8666
   6.750   0.9472   0.04181   0.03181  -0.0859   0.5509   0.8794
   7.250   0.9838   0.04262   0.03292  -0.0839   0.5345   0.9233
   7.500   0.9856   0.04454   0.03497  -0.0826   0.5222   1.0000
   7.750   1.0372   0.04342   0.03397  -0.0851   0.5178   1.0000
   8.000   1.0396   0.04583   0.03647  -0.0843   0.5050   1.0000
   8.500   1.0935   0.04675   0.03759  -0.0854   0.4879   1.0000
   8.750   1.0946   0.04922   0.04017  -0.0844   0.4753   1.0000
   9.000   1.1499   0.04714   0.03821  -0.0860   0.4708   1.0000
   9.250   1.1445   0.04997   0.04115  -0.0844   0.4576   1.0000
   9.500   1.1444   0.05251   0.04379  -0.0832   0.4450   1.0000
   9.750   1.1988   0.05002   0.04144  -0.0841   0.4396   1.0000
  10.000   1.1946   0.05277   0.04432  -0.0826   0.4266   1.0000
  10.250   1.1923   0.05551   0.04717  -0.0814   0.4138   1.0000
  10.500   1.2004   0.05726   0.04904  -0.0806   0.4023   1.0000
  10.750   1.2488   0.05473   0.04663  -0.0804   0.3947   1.0000
  11.250   1.2420   0.06051   0.05267  -0.0782   0.3688   1.0000
  11.500   1.2511   0.06209   0.05437  -0.0774   0.3568   1.0000
  11.750   1.2771   0.06163   0.05401  -0.0765   0.3459   1.0000
  12.000   1.2965   0.06189   0.05437  -0.0756   0.3338   1.0000
  12.250   1.2905   0.06524   0.05784  -0.0749   0.3205   1.0000
  12.500   1.2885   0.06820   0.06092  -0.0743   0.3075   1.0000
  12.750   1.2909   0.07069   0.06354  -0.0737   0.2947   1.0000
  13.000   1.2967   0.07270   0.06565  -0.0731   0.2820   1.0000
  13.250   1.3048   0.07441   0.06744  -0.0725   0.2693   1.0000
  13.500   1.3132   0.07607   0.06914  -0.0719   0.2565   1.0000
  13.750   1.3199   0.07799   0.07111  -0.0714   0.2437   1.0000
  14.000   1.3108   0.08241   0.07567  -0.0718   0.2314   1.0000
  14.250   1.3057   0.08633   0.07970  -0.0722   0.2195   1.0000
  14.500   1.3054   0.08958   0.08302  -0.0724   0.2079   1.0000
  14.750   1.3083   0.09230   0.08578  -0.0725   0.1963   1.0000
  15.000   1.3141   0.09452   0.08798  -0.0724   0.1849   1.0000
  15.250   1.3029   0.09985   0.09350  -0.0739   0.1749   1.0000
  15.500   1.2982   0.10413   0.09786  -0.0749   0.1650   1.0000
  15.750   1.3021   0.10683   0.10055  -0.0754   0.1551   1.0000
  16.000   1.2967   0.11137   0.10520  -0.0768   0.1460   1.0000
  16.250   1.2893   0.11645   0.11040  -0.0787   0.1378   1.0000
  16.500   1.2957   0.11869   0.11257  -0.0791   0.1288   1.0000
  16.750   1.2805   0.12560   0.11973  -0.0823   0.1220   1.0000
  17.000   1.2828   0.12878   0.12289  -0.0834   0.1140   1.0000
  17.250   1.2718   0.13505   0.12933  -0.0866   0.1075   1.0000
  17.500   1.2699   0.13924   0.13354  -0.0886   0.1004   1.0000
  17.750   1.2596   0.14552   0.13996  -0.0921   0.0943   1.0000
  18.000   1.2555   0.15038   0.14485  -0.0949   0.0878   1.0000
  18.250   1.2376   0.15899   0.15364  -0.1001   0.0834   1.0000
  18.500   1.2412   0.16195   0.15654  -0.1020   0.0763   1.0000
  18.750   1.2102   0.17502   0.16982  -0.1102   0.0746   1.0000
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