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EPPLER 560 AIRFOIL (e560-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 560 AIRFOIL (e560-il)
Reynolds number: 500,000
Max Cl/Cd: 105.59 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e560-il-500000.txt
Download as CSV file: xf-e560-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.250  -0.6343   0.11137   0.10835  -0.0545   1.0000   0.0198
 -16.000  -0.6704   0.10088   0.09766  -0.0601   1.0000   0.0194
 -15.750  -0.6869   0.09447   0.09114  -0.0635   1.0000   0.0196
 -15.500  -0.6999   0.08890   0.08547  -0.0662   1.0000   0.0196
 -15.250  -0.7111   0.08388   0.08035  -0.0686   1.0000   0.0196
 -15.000  -0.7207   0.07924   0.07562  -0.0707   1.0000   0.0197
 -14.750  -0.7290   0.07504   0.07134  -0.0725   1.0000   0.0198
 -14.500  -0.7364   0.07115   0.06737  -0.0740   1.0000   0.0199
 -14.250  -0.7437   0.06742   0.06357  -0.0753   1.0000   0.0200
 -14.000  -0.7503   0.06405   0.06013  -0.0763   1.0000   0.0200
 -13.750  -0.7577   0.06085   0.05686  -0.0770   1.0000   0.0201
 -13.500  -0.7656   0.05779   0.05375  -0.0775   1.0000   0.0202
 -13.250  -0.7736   0.05500   0.05091  -0.0776   1.0000   0.0202
 -13.000  -0.7837   0.05221   0.04807  -0.0774   1.0000   0.0203
 -12.750  -0.7950   0.04957   0.04539  -0.0768   1.0000   0.0203
 -12.500  -0.8103   0.04689   0.04265  -0.0759   1.0000   0.0204
 -12.250  -0.8265   0.04430   0.04002  -0.0749   0.9997   0.0205
 -12.000  -0.8098   0.04101   0.03664  -0.0807   0.9955   0.0207
 -11.750  -0.7961   0.03772   0.03324  -0.0862   0.9897   0.0209
 -11.500  -0.7713   0.03432   0.02973  -0.0933   0.9850   0.0210
 -11.250  -0.7466   0.03023   0.02550  -0.1015   0.9790   0.0214
 -11.000  -0.7135   0.02629   0.02142  -0.1108   0.9742   0.0219
 -10.750  -0.6772   0.02408   0.01912  -0.1167   0.9720   0.0224
 -10.500  -0.6525   0.02249   0.01745  -0.1187   0.9651   0.0230
 -10.250  -0.6171   0.02112   0.01600  -0.1222   0.9622   0.0237
 -10.000  -0.5794   0.01997   0.01475  -0.1257   0.9604   0.0246
  -9.750  -0.5539   0.01900   0.01369  -0.1263   0.9531   0.0253
  -9.500  -0.5186   0.01758   0.01221  -0.1295   0.9500   0.0267
  -9.250  -0.4810   0.01662   0.01119  -0.1323   0.9480   0.0282
  -9.000  -0.4533   0.01586   0.01034  -0.1328   0.9409   0.0297
  -8.750  -0.4183   0.01486   0.00932  -0.1350   0.9372   0.0331
  -8.500  -0.3814   0.01389   0.00835  -0.1374   0.9346   0.0410
  -8.250  -0.3521   0.01283   0.00741  -0.1385   0.9276   0.0636
  -8.000  -0.3169   0.01208   0.00674  -0.1404   0.9225   0.0841
  -7.750  -0.2761   0.01151   0.00620  -0.1432   0.9193   0.1004
  -7.500  -0.2421   0.01108   0.00577  -0.1445   0.9102   0.1136
  -7.250  -0.1972   0.01065   0.00534  -0.1481   0.9049   0.1276
  -7.000  -0.1547   0.01031   0.00500  -0.1512   0.8957   0.1413
  -6.500  -0.0664   0.00979   0.00442  -0.1580   0.8733   0.1684
  -6.250  -0.0299   0.00964   0.00421  -0.1598   0.8579   0.1802
  -6.000   0.0034   0.00956   0.00403  -0.1608   0.8413   0.1907
  -5.750   0.0339   0.00950   0.00389  -0.1612   0.8248   0.2002
  -5.500   0.0629   0.00945   0.00375  -0.1613   0.8085   0.2092
  -5.250   0.0911   0.00947   0.00366  -0.1612   0.7926   0.2186
  -5.000   0.1185   0.00942   0.00357  -0.1611   0.7772   0.2275
  -4.750   0.1460   0.00946   0.00348  -0.1608   0.7627   0.2355
  -4.500   0.1731   0.00941   0.00340  -0.1605   0.7486   0.2434
  -4.250   0.2003   0.00945   0.00332  -0.1602   0.7349   0.2505
  -4.000   0.2272   0.00942   0.00324  -0.1599   0.7213   0.2577
  -3.750   0.2543   0.00944   0.00319  -0.1596   0.7085   0.2649
  -3.500   0.2814   0.00942   0.00312  -0.1593   0.6961   0.2715
  -3.250   0.3083   0.00945   0.00308  -0.1590   0.6839   0.2787
  -3.000   0.3354   0.00950   0.00303  -0.1586   0.6718   0.2854
  -2.750   0.3625   0.00948   0.00301  -0.1584   0.6604   0.2924
  -2.500   0.3896   0.00955   0.00298  -0.1581   0.6494   0.2994
  -2.250   0.4166   0.00955   0.00296  -0.1578   0.6382   0.3062
  -2.000   0.4437   0.00959   0.00296  -0.1575   0.6273   0.3134
  -1.750   0.4708   0.00964   0.00294  -0.1572   0.6173   0.3202
  -1.500   0.4979   0.00966   0.00295  -0.1570   0.6069   0.3270
  -1.250   0.5251   0.00975   0.00296  -0.1567   0.5971   0.3342
  -1.000   0.5519   0.00978   0.00297  -0.1564   0.5872   0.3413
  -0.750   0.5792   0.00983   0.00300  -0.1561   0.5778   0.3485
  -0.250   0.6333   0.00994   0.00307  -0.1556   0.5599   0.3632
   0.000   0.6599   0.01006   0.00310  -0.1552   0.5512   0.3703
   0.250   0.6872   0.01007   0.00315  -0.1550   0.5425   0.3780
   0.500   0.7138   0.01021   0.00321  -0.1547   0.5347   0.3860
   0.750   0.7411   0.01022   0.00327  -0.1545   0.5266   0.3939
   1.000   0.7675   0.01036   0.00334  -0.1541   0.5189   0.4021
   1.250   0.7947   0.01039   0.00342  -0.1539   0.5112   0.4106
   1.500   0.8212   0.01051   0.00350  -0.1535   0.5039   0.4195
   1.750   0.8482   0.01058   0.00359  -0.1533   0.4972   0.4281
   2.000   0.8747   0.01068   0.00369  -0.1530   0.4900   0.4380
   2.250   0.9011   0.01079   0.00380  -0.1526   0.4834   0.4480
   2.500   0.9279   0.01086   0.00391  -0.1524   0.4766   0.4586
   2.750   0.9540   0.01100   0.00403  -0.1520   0.4705   0.4699
   3.000   0.9807   0.01108   0.00417  -0.1517   0.4645   0.4826
   3.250   1.0070   0.01118   0.00430  -0.1513   0.4581   0.4963
   3.500   1.0327   0.01135   0.00446  -0.1509   0.4522   0.5113
   3.750   1.0593   0.01141   0.00461  -0.1506   0.4468   0.5291
   4.000   1.0853   0.01150   0.00477  -0.1503   0.4409   0.5501
   4.250   1.1106   0.01169   0.00497  -0.1498   0.4353   0.5747
   4.500   1.1370   0.01172   0.00515  -0.1495   0.4301   0.6044
   4.750   1.1625   0.01181   0.00534  -0.1490   0.4247   0.6423
   5.000   1.1870   0.01197   0.00559  -0.1484   0.4193   0.6898
   5.250   1.2116   0.01197   0.00581  -0.1477   0.4144   0.7523
   5.500   1.2311   0.01192   0.00601  -0.1458   0.4094   0.8473
   5.750   1.2478   0.01191   0.00611  -0.1433   0.4045   1.0000
   6.000   1.2729   0.01212   0.00632  -0.1428   0.3996   1.0000
   6.250   1.2977   0.01229   0.00650  -0.1422   0.3943   1.0000
   6.500   1.3209   0.01254   0.00671  -0.1414   0.3891   1.0000
   6.750   1.3443   0.01278   0.00695  -0.1405   0.3842   1.0000
   7.000   1.3674   0.01295   0.00716  -0.1396   0.3790   1.0000
   7.250   1.3893   0.01321   0.00739  -0.1386   0.3737   1.0000
   7.500   1.4112   0.01350   0.00767  -0.1375   0.3686   1.0000
   7.750   1.4333   0.01368   0.00790  -0.1364   0.3632   1.0000
   8.000   1.4539   0.01395   0.00816  -0.1352   0.3576   1.0000
   8.250   1.4746   0.01426   0.00847  -0.1339   0.3522   1.0000
   8.500   1.4960   0.01447   0.00874  -0.1328   0.3466   1.0000
   8.750   1.5154   0.01479   0.00905  -0.1313   0.3410   1.0000
   9.000   1.5350   0.01511   0.00939  -0.1299   0.3354   1.0000
   9.250   1.5552   0.01538   0.00971  -0.1287   0.3294   1.0000
   9.500   1.5724   0.01579   0.01009  -0.1269   0.3233   1.0000
   9.750   1.5918   0.01609   0.01045  -0.1256   0.3168   1.0000
  10.000   1.6085   0.01649   0.01086  -0.1238   0.3096   1.0000
  10.250   1.6256   0.01690   0.01130  -0.1221   0.3025   1.0000
  10.500   1.6414   0.01736   0.01177  -0.1203   0.2945   1.0000
  10.750   1.6567   0.01785   0.01228  -0.1185   0.2858   1.0000
  11.000   1.6694   0.01847   0.01289  -0.1163   0.2769   1.0000
  11.250   1.6841   0.01904   0.01349  -0.1145   0.2672   1.0000
  11.500   1.6952   0.01979   0.01423  -0.1123   0.2578   1.0000
  11.750   1.7057   0.02059   0.01504  -0.1101   0.2472   1.0000
  12.000   1.7161   0.02145   0.01591  -0.1079   0.2364   1.0000
  12.250   1.7236   0.02251   0.01695  -0.1056   0.2253   1.0000
  12.500   1.7286   0.02377   0.01818  -0.1031   0.2137   1.0000
  12.750   1.7326   0.02516   0.01956  -0.1007   0.2016   1.0000
  13.000   1.7359   0.02668   0.02107  -0.0984   0.1893   1.0000
  13.250   1.7370   0.02844   0.02281  -0.0961   0.1772   1.0000
  13.500   1.7362   0.03045   0.02481  -0.0940   0.1657   1.0000
  13.750   1.7329   0.03278   0.02712  -0.0919   0.1540   1.0000
  14.000   1.7283   0.03538   0.02971  -0.0901   0.1434   1.0000
  14.250   1.7248   0.03803   0.03235  -0.0885   0.1331   1.0000
  14.500   1.7207   0.04088   0.03523  -0.0873   0.1241   1.0000
  14.750   1.7141   0.04412   0.03848  -0.0862   0.1165   1.0000
  15.000   1.7096   0.04731   0.04171  -0.0855   0.1086   1.0000
  15.250   1.7026   0.05089   0.04533  -0.0849   0.1022   1.0000
  15.500   1.6959   0.05460   0.04908  -0.0846   0.0955   1.0000
  15.750   1.6883   0.05855   0.05308  -0.0845   0.0899   1.0000
  16.000   1.6804   0.06266   0.05724  -0.0846   0.0843   1.0000
  16.250   1.6715   0.06706   0.06169  -0.0849   0.0795   1.0000
  16.500   1.6646   0.07130   0.06600  -0.0854   0.0748   1.0000
  17.000   1.6473   0.08057   0.07540  -0.0870   0.0663   1.0000
  17.250   1.6373   0.08558   0.08046  -0.0880   0.0623   1.0000
  17.500   1.6288   0.09047   0.08541  -0.0892   0.0587   1.0000
  17.750   1.6212   0.09527   0.09028  -0.0905   0.0551   1.0000
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