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EPPLER 560 AIRFOIL (e560-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 560 AIRFOIL (e560-il)
Reynolds number: 200,000
Max Cl/Cd: 72.78 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e560-il-200000.txt
Download as CSV file: xf-e560-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 560 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.6482   0.07146   0.06694  -0.0792   1.0000   0.0355
 -13.000  -0.6719   0.06586   0.06122  -0.0819   1.0000   0.0354
 -12.750  -0.6914   0.06122   0.05648  -0.0838   1.0000   0.0353
 -12.500  -0.7133   0.05683   0.05197  -0.0854   1.0000   0.0354
 -12.250  -0.7333   0.05314   0.04818  -0.0861   1.0000   0.0354
 -12.000  -0.7522   0.05013   0.04508  -0.0857   1.0000   0.0354
 -11.750  -0.7762   0.04759   0.04248  -0.0843   1.0000   0.0354
 -11.500  -0.8005   0.04546   0.04031  -0.0820   1.0000   0.0353
 -11.250  -0.8156   0.04260   0.03728  -0.0830   1.0000   0.0355
 -11.000  -0.8205   0.04021   0.03478  -0.0825   1.0000   0.0358
 -10.750  -0.8190   0.03822   0.03273  -0.0815   1.0000   0.0362
 -10.500  -0.7863   0.03629   0.03080  -0.0855   0.9956   0.0374
 -10.250  -0.7517   0.03435   0.02873  -0.0899   0.9904   0.0386
 -10.000  -0.7165   0.03243   0.02665  -0.0940   0.9852   0.0398
  -9.750  -0.6819   0.03070   0.02473  -0.0975   0.9797   0.0411
  -9.500  -0.6474   0.02890   0.02285  -0.1008   0.9743   0.0427
  -9.250  -0.6127   0.02737   0.02134  -0.1041   0.9687   0.0448
  -8.750  -0.5378   0.02433   0.01819  -0.1113   0.9583   0.0522
  -8.250  -0.4600   0.02100   0.01486  -0.1191   0.9480   0.0795
  -8.000  -0.4268   0.01989   0.01376  -0.1213   0.9401   0.1030
  -7.750  -0.3849   0.01914   0.01301  -0.1247   0.9358   0.1219
  -7.500  -0.3472   0.01863   0.01245  -0.1270   0.9300   0.1377
  -7.250  -0.3097   0.01815   0.01192  -0.1290   0.9235   0.1517
  -7.000  -0.2662   0.01769   0.01140  -0.1321   0.9202   0.1667
  -6.750  -0.2319   0.01735   0.01103  -0.1334   0.9124   0.1800
  -6.500  -0.1914   0.01699   0.01063  -0.1358   0.9075   0.1944
  -6.250  -0.1469   0.01660   0.01019  -0.1388   0.9045   0.2087
  -6.000  -0.1119   0.01631   0.00979  -0.1400   0.8959   0.2207
  -5.750  -0.0678   0.01595   0.00940  -0.1430   0.8909   0.2324
  -5.500  -0.0198   0.01556   0.00901  -0.1467   0.8864   0.2437
  -5.250   0.0170   0.01525   0.00861  -0.1483   0.8759   0.2542
  -5.000   0.0607   0.01502   0.00829  -0.1512   0.8676   0.2652
  -4.750   0.1009   0.01474   0.00799  -0.1534   0.8570   0.2743
  -4.500   0.1372   0.01459   0.00766  -0.1549   0.8441   0.2845
  -4.250   0.1730   0.01442   0.00751  -0.1562   0.8315   0.2925
  -4.000   0.2089   0.01429   0.00719  -0.1576   0.8190   0.3022
  -3.750   0.2409   0.01422   0.00710  -0.1582   0.8055   0.3099
  -3.500   0.2702   0.01416   0.00688  -0.1583   0.7911   0.3187
  -3.250   0.2986   0.01412   0.00684  -0.1582   0.7773   0.3259
  -3.000   0.3283   0.01412   0.00665  -0.1584   0.7641   0.3349
  -2.750   0.3571   0.01407   0.00659  -0.1583   0.7515   0.3420
  -2.500   0.3857   0.01410   0.00645  -0.1583   0.7388   0.3509
  -2.250   0.4120   0.01404   0.00641  -0.1578   0.7259   0.3577
  -2.000   0.4399   0.01409   0.00634  -0.1576   0.7138   0.3665
  -1.750   0.4685   0.01408   0.00625  -0.1576   0.7027   0.3740
  -1.500   0.4946   0.01410   0.00623  -0.1571   0.6905   0.3822
  -1.250   0.5218   0.01411   0.00618  -0.1569   0.6793   0.3903
  -1.000   0.5502   0.01417   0.00615  -0.1568   0.6691   0.3989
  -0.750   0.5760   0.01417   0.00612  -0.1563   0.6575   0.4071
  -0.500   0.6032   0.01423   0.00616  -0.1560   0.6474   0.4159
  -0.250   0.6308   0.01428   0.00613  -0.1558   0.6377   0.4249
   0.000   0.6569   0.01434   0.00619  -0.1554   0.6274   0.4338
   0.250   0.6853   0.01442   0.00618  -0.1554   0.6186   0.4433
   0.500   0.7108   0.01447   0.00626  -0.1548   0.6085   0.4534
   0.750   0.7386   0.01456   0.00631  -0.1547   0.6003   0.4627
   1.000   0.7648   0.01464   0.00637  -0.1543   0.5908   0.4739
   1.250   0.7921   0.01474   0.00647  -0.1541   0.5828   0.4843
   1.500   0.8181   0.01480   0.00657  -0.1537   0.5740   0.4954
   1.750   0.8462   0.01496   0.00666  -0.1536   0.5667   0.5083
   2.000   0.8715   0.01503   0.00682  -0.1531   0.5582   0.5206
   2.250   0.8998   0.01518   0.00693  -0.1531   0.5513   0.5343
   2.500   0.9245   0.01526   0.00711  -0.1524   0.5430   0.5488
   2.750   0.9523   0.01540   0.00725  -0.1524   0.5365   0.5656
   3.000   0.9777   0.01552   0.00748  -0.1519   0.5292   0.5839
   3.250   1.0039   0.01563   0.00764  -0.1515   0.5222   0.6049
   3.500   1.0306   0.01580   0.00787  -0.1512   0.5159   0.6301
   3.750   1.0549   0.01589   0.00812  -0.1505   0.5090   0.6600
   4.000   1.0812   0.01601   0.00832  -0.1500   0.5032   0.6988
   4.250   1.1029   0.01608   0.00863  -0.1487   0.4968   0.7512
   4.500   1.1196   0.01603   0.00880  -0.1460   0.4908   0.8360
   4.750   1.1421   0.01603   0.00882  -0.1446   0.4857   1.0000
   5.000   1.1675   0.01632   0.00914  -0.1443   0.4792   1.0000
   5.250   1.1944   0.01659   0.00937  -0.1442   0.4731   1.0000
   5.500   1.2238   0.01697   0.00963  -0.1446   0.4679   1.0000
   5.750   1.2469   0.01725   0.01000  -0.1438   0.4615   1.0000
   6.000   1.2733   0.01754   0.01026  -0.1436   0.4558   1.0000
   6.250   1.3011   0.01793   0.01058  -0.1436   0.4506   1.0000
   6.500   1.3234   0.01823   0.01098  -0.1427   0.4444   1.0000
   6.750   1.3494   0.01854   0.01125  -0.1424   0.4388   1.0000
   7.000   1.3758   0.01894   0.01163  -0.1422   0.4335   1.0000
   7.250   1.3970   0.01926   0.01205  -0.1411   0.4273   1.0000
   7.500   1.4227   0.01957   0.01233  -0.1407   0.4218   1.0000
   7.750   1.4466   0.01997   0.01276  -0.1401   0.4162   1.0000
   8.000   1.4672   0.02030   0.01317  -0.1389   0.4099   1.0000
   8.250   1.4927   0.02062   0.01345  -0.1385   0.4043   1.0000
   8.500   1.5128   0.02103   0.01395  -0.1372   0.3983   1.0000
   8.750   1.5328   0.02134   0.01432  -0.1359   0.3919   1.0000
   9.000   1.5597   0.02173   0.01463  -0.1358   0.3861   1.0000
   9.250   1.5727   0.02209   0.01517  -0.1333   0.3795   1.0000
   9.500   1.5928   0.02240   0.01549  -0.1320   0.3733   1.0000
   9.750   1.6118   0.02283   0.01596  -0.1306   0.3671   1.0000
  10.000   1.6255   0.02320   0.01644  -0.1282   0.3604   1.0000
  10.500   1.6524   0.02399   0.01735  -0.1234   0.3474   1.0000
  10.750   1.6650   0.02436   0.01774  -0.1209   0.3408   1.0000
  11.000   1.6747   0.02487   0.01832  -0.1181   0.3338   1.0000
  11.250   1.6819   0.02537   0.01891  -0.1148   0.3267   1.0000
  11.500   1.6926   0.02594   0.01950  -0.1124   0.3196   1.0000
  11.750   1.6964   0.02662   0.02032  -0.1089   0.3121   1.0000
  12.000   1.7060   0.02732   0.02101  -0.1065   0.3049   1.0000
  12.250   1.7074   0.02824   0.02208  -0.1031   0.2969   1.0000
  12.500   1.7135   0.02915   0.02300  -0.1006   0.2892   1.0000
  12.750   1.7139   0.03034   0.02432  -0.0975   0.2806   1.0000
  13.000   1.7160   0.03161   0.02565  -0.0949   0.2722   1.0000
  13.250   1.7154   0.03311   0.02721  -0.0923   0.2630   1.0000
  13.500   1.7142   0.03483   0.02903  -0.0900   0.2534   1.0000
  13.750   1.7116   0.03677   0.03096  -0.0878   0.2441   1.0000
  14.000   1.7075   0.03901   0.03330  -0.0858   0.2336   1.0000
  14.250   1.7022   0.04153   0.03588  -0.0842   0.2231   1.0000
  14.500   1.6951   0.04439   0.03875  -0.0827   0.2130   1.0000
  14.750   1.6866   0.04759   0.04198  -0.0815   0.2024   1.0000
  15.000   1.6782   0.05103   0.04548  -0.0807   0.1917   1.0000
  15.250   1.6678   0.05485   0.04932  -0.0802   0.1816   1.0000
  15.500   1.6551   0.05910   0.05357  -0.0799   0.1721   1.0000
  15.750   1.6449   0.06333   0.05788  -0.0800   0.1621   1.0000
  16.000   1.6335   0.06785   0.06244  -0.0803   0.1533   1.0000
  16.250   1.6200   0.07278   0.06736  -0.0809   0.1450   1.0000
  16.500   1.6103   0.07745   0.07212  -0.0816   0.1367   1.0000
  16.750   1.5974   0.08259   0.07725  -0.0826   0.1296   1.0000
  17.000   1.5881   0.08743   0.08218  -0.0837   0.1221   1.0000
  17.250   1.5768   0.09258   0.08733  -0.0850   0.1159   1.0000
  17.500   1.5683   0.09749   0.09234  -0.0863   0.1092   1.0000
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