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EPPLER 559 AIRFOIL (e559-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 559 AIRFOIL (e559-il)
Reynolds number: 500,000
Max Cl/Cd: 103.11 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e559-il-500000.txt
Download as CSV file: xf-e559-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 559 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.250  -0.6447   0.12609   0.12313  -0.0435   1.0000   0.0170
 -17.000  -0.6793   0.11501   0.11187  -0.0494   1.0000   0.0170
 -16.750  -0.7015   0.10699   0.10370  -0.0536   1.0000   0.0169
 -16.500  -0.7195   0.09997   0.09656  -0.0574   1.0000   0.0170
 -16.250  -0.7340   0.09386   0.09032  -0.0606   1.0000   0.0170
 -16.000  -0.7463   0.08828   0.08462  -0.0635   1.0000   0.0171
 -15.750  -0.7574   0.08299   0.07921  -0.0664   1.0000   0.0173
 -15.500  -0.7658   0.07839   0.07451  -0.0686   1.0000   0.0173
 -15.250  -0.7751   0.07374   0.06975  -0.0711   1.0000   0.0174
 -15.000  -0.7813   0.06993   0.06585  -0.0726   1.0000   0.0175
 -14.750  -0.7845   0.06721   0.06313  -0.0726   1.0000   0.0180
 -14.500  -0.7865   0.06426   0.06017  -0.0735   1.0000   0.0183
 -14.250  -0.7904   0.06126   0.05711  -0.0742   1.0000   0.0184
 -14.000  -0.7950   0.05826   0.05408  -0.0750   1.0000   0.0186
 -13.750  -0.8000   0.05527   0.05105  -0.0758   1.0000   0.0189
 -13.500  -0.8057   0.05236   0.04809  -0.0763   1.0000   0.0191
 -13.250  -0.8118   0.04950   0.04518  -0.0768   1.0000   0.0193
 -13.000  -0.8201   0.04662   0.04225  -0.0769   1.0000   0.0195
 -12.750  -0.8290   0.04386   0.03944  -0.0768   1.0000   0.0198
 -12.500  -0.8397   0.04124   0.03677  -0.0761   1.0000   0.0199
 -12.250  -0.8544   0.03866   0.03413  -0.0750   1.0000   0.0201
 -12.000  -0.8775   0.03628   0.03172  -0.0725   1.0000   0.0201
 -11.750  -0.8823   0.03335   0.02869  -0.0743   0.9981   0.0204
 -11.500  -0.8482   0.03014   0.02531  -0.0830   0.9942   0.0209
 -11.250  -0.8205   0.02700   0.02204  -0.0893   0.9888   0.0216
 -11.000  -0.7878   0.02496   0.01994  -0.0941   0.9850   0.0224
 -10.750  -0.7513   0.02351   0.01841  -0.0984   0.9829   0.0233
 -10.500  -0.7237   0.02226   0.01708  -0.1001   0.9769   0.0242
 -10.250  -0.6883   0.02132   0.01603  -0.1029   0.9739   0.0251
 -10.000  -0.6530   0.01957   0.01423  -0.1068   0.9715   0.0266
  -9.750  -0.6265   0.01858   0.01319  -0.1076   0.9645   0.0277
  -9.500  -0.5908   0.01769   0.01222  -0.1100   0.9613   0.0291
  -9.250  -0.5536   0.01662   0.01109  -0.1129   0.9591   0.0310
  -9.000  -0.5274   0.01581   0.01024  -0.1132   0.9511   0.0331
  -8.750  -0.4913   0.01499   0.00936  -0.1154   0.9477   0.0361
  -8.500  -0.4601   0.01419   0.00854  -0.1165   0.9418   0.0408
  -8.250  -0.4284   0.01319   0.00761  -0.1179   0.9358   0.0538
  -8.000  -0.3922   0.01218   0.00675  -0.1202   0.9322   0.0813
  -7.750  -0.3612   0.01160   0.00622  -0.1211   0.9232   0.1009
  -7.500  -0.3204   0.01102   0.00569  -0.1240   0.9182   0.1198
  -7.250  -0.2806   0.01059   0.00529  -0.1265   0.9099   0.1371
  -7.000  -0.2334   0.01022   0.00492  -0.1306   0.9025   0.1548
  -6.750  -0.1912   0.00993   0.00461  -0.1336   0.8900   0.1697
  -6.500  -0.1510   0.00971   0.00434  -0.1361   0.8749   0.1838
  -6.250  -0.1156   0.00956   0.00413  -0.1376   0.8577   0.1973
  -6.000  -0.0839   0.00947   0.00395  -0.1383   0.8395   0.2085
  -5.750  -0.0543   0.00945   0.00381  -0.1385   0.8216   0.2190
  -5.500  -0.0263   0.00938   0.00369  -0.1384   0.8042   0.2289
  -5.250   0.0012   0.00936   0.00357  -0.1382   0.7875   0.2382
  -5.000   0.0285   0.00936   0.00349  -0.1379   0.7716   0.2477
  -4.750   0.0555   0.00933   0.00340  -0.1376   0.7563   0.2564
  -4.500   0.0826   0.00935   0.00331  -0.1373   0.7414   0.2646
  -4.250   0.1094   0.00932   0.00323  -0.1370   0.7272   0.2721
  -4.000   0.1365   0.00934   0.00316  -0.1366   0.7138   0.2797
  -3.500   0.1905   0.00934   0.00303  -0.1360   0.6871   0.2943
  -3.250   0.2177   0.00935   0.00296  -0.1357   0.6747   0.3010
  -3.000   0.2448   0.00935   0.00293  -0.1354   0.6630   0.3084
  -2.750   0.2719   0.00941   0.00288  -0.1351   0.6510   0.3154
  -2.500   0.2991   0.00938   0.00285  -0.1349   0.6393   0.3227
  -2.250   0.3263   0.00944   0.00283  -0.1346   0.6283   0.3300
  -2.000   0.3534   0.00945   0.00280  -0.1343   0.6175   0.3369
  -1.750   0.3808   0.00948   0.00280  -0.1341   0.6069   0.3444
  -1.500   0.4080   0.00954   0.00279  -0.1338   0.5967   0.3513
  -1.250   0.4352   0.00955   0.00280  -0.1336   0.5863   0.3585
  -1.000   0.4626   0.00963   0.00280  -0.1333   0.5769   0.3661
  -0.750   0.4896   0.00965   0.00282  -0.1331   0.5673   0.3732
  -0.500   0.5170   0.00970   0.00284  -0.1329   0.5581   0.3809
  -0.250   0.5438   0.00977   0.00286  -0.1326   0.5488   0.3883
   0.000   0.5714   0.00981   0.00291  -0.1324   0.5401   0.3963
   0.500   0.6257   0.00992   0.00299  -0.1319   0.5233   0.4122
   1.000   0.6798   0.01006   0.00311  -0.1314   0.5072   0.4289
   1.250   0.7065   0.01017   0.00317  -0.1311   0.4997   0.4379
   1.500   0.7338   0.01022   0.00326  -0.1309   0.4924   0.4474
   1.750   0.7605   0.01031   0.00333  -0.1306   0.4848   0.4567
   2.000   0.7874   0.01039   0.00343  -0.1304   0.4780   0.4671
   2.250   0.8143   0.01046   0.00352  -0.1301   0.4711   0.4779
   2.500   0.8406   0.01060   0.00363  -0.1298   0.4648   0.4898
   2.750   0.8678   0.01064   0.00375  -0.1296   0.4583   0.5026
   3.000   0.8941   0.01074   0.00387  -0.1292   0.4517   0.5169
   3.250   0.9207   0.01085   0.00401  -0.1289   0.4458   0.5329
   3.500   0.9474   0.01091   0.00415  -0.1287   0.4399   0.5511
   3.750   0.9733   0.01104   0.00429  -0.1283   0.4341   0.5723
   4.000   0.9997   0.01111   0.00446  -0.1280   0.4284   0.5979
   4.250   1.0259   0.01118   0.00463  -0.1276   0.4226   0.6284
   4.500   1.0512   0.01130   0.00482  -0.1271   0.4172   0.6651
   4.750   1.0767   0.01134   0.00503  -0.1266   0.4120   0.7123
   5.000   1.1009   0.01135   0.00523  -0.1258   0.4065   0.7721
   5.250   1.1197   0.01135   0.00542  -0.1237   0.4015   0.8575
   5.500   1.1407   0.01131   0.00552  -0.1221   0.3966   1.0000
   5.750   1.1666   0.01147   0.00569  -0.1217   0.3911   1.0000
   6.000   1.1916   0.01170   0.00588  -0.1212   0.3859   1.0000
   6.250   1.2168   0.01193   0.00610  -0.1208   0.3809   1.0000
   6.500   1.2421   0.01209   0.00629  -0.1203   0.3755   1.0000
   6.750   1.2662   0.01232   0.00650  -0.1196   0.3702   1.0000
   7.000   1.2902   0.01258   0.00674  -0.1190   0.3651   1.0000
   7.250   1.3146   0.01275   0.00695  -0.1183   0.3599   1.0000
   7.500   1.3376   0.01299   0.00719  -0.1175   0.3545   1.0000
   7.750   1.3601   0.01327   0.00745  -0.1165   0.3491   1.0000
   8.000   1.3827   0.01344   0.00768  -0.1156   0.3437   1.0000
   8.250   1.4032   0.01371   0.00793  -0.1143   0.3379   1.0000
   8.500   1.4238   0.01398   0.00822  -0.1130   0.3324   1.0000
   8.750   1.4449   0.01420   0.00849  -0.1118   0.3264   1.0000
   9.000   1.4633   0.01454   0.00879  -0.1102   0.3203   1.0000
   9.250   1.4841   0.01478   0.00910  -0.1090   0.3143   1.0000
   9.500   1.5030   0.01509   0.00942  -0.1075   0.3079   1.0000
   9.750   1.5206   0.01546   0.00980  -0.1058   0.3015   1.0000
  10.000   1.5400   0.01576   0.01015  -0.1045   0.2945   1.0000
  10.500   1.5744   0.01654   0.01098  -0.1012   0.2804   1.0000
  11.000   1.6054   0.01748   0.01195  -0.0975   0.2641   1.0000
  11.250   1.6181   0.01809   0.01255  -0.0954   0.2557   1.0000
  11.500   1.6321   0.01867   0.01316  -0.0935   0.2461   1.0000
  11.750   1.6441   0.01936   0.01386  -0.0914   0.2366   1.0000
  12.000   1.6527   0.02024   0.01472  -0.0890   0.2264   1.0000
  12.250   1.6615   0.02115   0.01563  -0.0867   0.2144   1.0000
  12.500   1.6678   0.02226   0.01672  -0.0844   0.2015   1.0000
  12.750   1.6721   0.02354   0.01798  -0.0819   0.1888   1.0000
  13.000   1.6744   0.02503   0.01944  -0.0795   0.1767   1.0000
  13.250   1.6741   0.02680   0.02118  -0.0771   0.1641   1.0000
  13.500   1.6721   0.02880   0.02316  -0.0749   0.1522   1.0000
  13.750   1.6683   0.03110   0.02543  -0.0729   0.1407   1.0000
  14.000   1.6665   0.03338   0.02772  -0.0712   0.1306   1.0000
  14.250   1.6631   0.03594   0.03029  -0.0698   0.1213   1.0000
  14.500   1.6576   0.03883   0.03319  -0.0686   0.1134   1.0000
  14.750   1.6530   0.04180   0.03619  -0.0677   0.1054   1.0000
  15.000   1.6479   0.04496   0.03939  -0.0670   0.0994   1.0000
  15.250   1.6411   0.04845   0.04292  -0.0666   0.0928   1.0000
  15.500   1.6343   0.05207   0.04659  -0.0664   0.0874   1.0000
  15.750   1.6268   0.05593   0.05050  -0.0664   0.0820   1.0000
  16.000   1.6179   0.06009   0.05472  -0.0667   0.0775   1.0000
  16.250   1.6113   0.06411   0.05880  -0.0671   0.0730   1.0000
  16.500   1.5999   0.06887   0.06361  -0.0678   0.0689   1.0000
  16.750   1.5933   0.07313   0.06796  -0.0686   0.0653   1.0000
  17.000   1.5841   0.07783   0.07272  -0.0696   0.0617   1.0000
  17.250   1.5720   0.08309   0.07803  -0.0709   0.0583   1.0000
  17.500   1.5666   0.08746   0.08249  -0.0720   0.0552   1.0000
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