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EPPLER 678 AIRFOIL (e678-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 678 AIRFOIL (e678-il)
Reynolds number: 200,000
Max Cl/Cd: 78.13 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e678-il-200000-n5.txt
Download as CSV file: xf-e678-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 678 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.0939   0.09179   0.08777  -0.1243   0.9309   0.0166
 -10.000  -0.0983   0.08705   0.08306  -0.1261   0.9279   0.0168
  -9.750  -0.0976   0.08202   0.07804  -0.1294   0.9257   0.0167
  -9.500  -0.0945   0.07657   0.07261  -0.1337   0.9238   0.0165
  -9.250  -0.1108   0.07156   0.06764  -0.1345   0.9185   0.0165
  -9.000  -0.1302   0.06499   0.06111  -0.1370   0.9130   0.0161
  -8.750  -0.1728   0.05159   0.04748  -0.1483   0.9081   0.0154
  -8.500  -0.2149   0.04897   0.04478  -0.1427   0.8962   0.0150
  -8.250  -0.2313   0.04503   0.04060  -0.1418   0.8894   0.0151
  -8.000  -0.2417   0.04122   0.03646  -0.1403   0.8820   0.0152
  -7.750  -0.2328   0.03581   0.03045  -0.1423   0.8791   0.0151
  -7.500  -0.2370   0.03347   0.02779  -0.1386   0.8696   0.0151
  -7.250  -0.2156   0.03035   0.02419  -0.1396   0.8663   0.0151
  -7.000  -0.1872   0.02782   0.02124  -0.1411   0.8644   0.0153
  -6.750  -0.1754   0.02643   0.01960  -0.1389   0.8567   0.0155
  -6.500  -0.1512   0.02486   0.01776  -0.1389   0.8523   0.0159
  -6.250  -0.1207   0.02334   0.01600  -0.1400   0.8499   0.0163
  -5.750  -0.0793   0.02144   0.01378  -0.1380   0.8365   0.0172
  -5.250  -0.0357   0.02004   0.01230  -0.1367   0.8208   0.0189
  -5.000  -0.0181   0.01968   0.01187  -0.1352   0.8085   0.0204
  -4.750   0.0080   0.01903   0.01111  -0.1352   0.8006   0.0214
  -4.500   0.0361   0.01835   0.01040  -0.1358   0.7929   0.0226
  -4.250   0.0672   0.01772   0.00970  -0.1368   0.7870   0.0246
  -4.000   0.0997   0.01710   0.00899  -0.1380   0.7812   0.0275
  -3.750   0.1358   0.01641   0.00827  -0.1399   0.7774   0.0356
  -3.500   0.1715   0.01573   0.00763  -0.1418   0.7725   0.0568
  -3.250   0.2089   0.01508   0.00707  -0.1441   0.7680   0.0910
  -3.000   0.2500   0.01418   0.00654  -0.1475   0.7643   0.1843
  -2.750   0.2924   0.01329   0.00607  -0.1513   0.7605   0.3146
  -2.500   0.3332   0.01263   0.00574  -0.1545   0.7562   0.4330
  -2.250   0.3722   0.01218   0.00554  -0.1570   0.7522   0.5332
  -2.000   0.4088   0.01195   0.00549  -0.1586   0.7485   0.6135
  -1.750   0.4417   0.01196   0.00547  -0.1594   0.7441   0.6570
  -1.500   0.4758   0.01200   0.00543  -0.1606   0.7400   0.6841
  -1.250   0.5122   0.01206   0.00536  -0.1624   0.7362   0.7048
  -0.750   0.5782   0.01231   0.00543  -0.1645   0.7286   0.7356
  -0.500   0.6075   0.01246   0.00553  -0.1648   0.7250   0.7464
  -0.250   0.6407   0.01259   0.00556  -0.1661   0.7218   0.7562
   0.000   0.6733   0.01273   0.00563  -0.1671   0.7190   0.7634
   0.250   0.7091   0.01286   0.00565  -0.1690   0.7163   0.7715
   0.500   0.7319   0.01301   0.00581  -0.1681   0.7127   0.7776
   0.750   0.7596   0.01316   0.00593  -0.1683   0.7094   0.7848
   1.000   0.7876   0.01329   0.00605  -0.1686   0.7065   0.7901
   1.250   0.8176   0.01343   0.00616  -0.1692   0.7037   0.7951
   1.500   0.8518   0.01359   0.00625  -0.1709   0.7011   0.8005
   1.750   0.8798   0.01374   0.00640  -0.1712   0.6982   0.8050
   2.000   0.9024   0.01389   0.00660  -0.1703   0.6948   0.8093
   2.250   0.9284   0.01405   0.00677  -0.1702   0.6911   0.8142
   2.500   0.9581   0.01422   0.00691  -0.1710   0.6874   0.8189
   2.750   0.9898   0.01437   0.00704  -0.1720   0.6838   0.8223
   3.000   1.0100   0.01453   0.00727  -0.1707   0.6794   0.8268
   3.250   1.0332   0.01470   0.00748  -0.1700   0.6748   0.8318
   3.500   1.0599   0.01485   0.00765  -0.1700   0.6706   0.8359
   3.750   1.0908   0.01500   0.00779  -0.1709   0.6670   0.8397
   4.000   1.1069   0.01517   0.00806  -0.1688   0.6620   0.8448
   4.250   1.1296   0.01534   0.00828  -0.1681   0.6569   0.8496
   4.500   1.1553   0.01545   0.00843  -0.1678   0.6524   0.8531
   4.750   1.1747   0.01560   0.00866  -0.1664   0.6472   0.8576
   5.000   1.1917   0.01575   0.00889  -0.1645   0.6415   0.8625
   5.250   1.2161   0.01586   0.00905  -0.1640   0.6363   0.8663
   5.500   1.2305   0.01600   0.00929  -0.1616   0.6304   0.8709
   5.750   1.2462   0.01617   0.00954  -0.1594   0.6237   0.8763
   6.000   1.2682   0.01629   0.00970  -0.1585   0.6173   0.8807
   6.250   1.2777   0.01651   0.01005  -0.1551   0.6094   0.8863
   6.500   1.2985   0.01662   0.01021  -0.1540   0.6023   0.8920
   6.750   1.3077   0.01689   0.01061  -0.1507   0.5932   0.8988
   7.000   1.3230   0.01708   0.01087  -0.1485   0.5843   0.9057
   7.250   1.3351   0.01731   0.01120  -0.1458   0.5739   0.9138
   7.500   1.3447   0.01761   0.01160  -0.1426   0.5620   0.9254
   7.750   1.3542   0.01788   0.01196  -0.1395   0.5483   0.9456
   8.000   1.3655   0.01819   0.01232  -0.1369   0.5312   1.0000
   8.250   1.3785   0.01872   0.01283  -0.1348   0.5094   1.0000
   8.500   1.3885   0.01940   0.01342  -0.1322   0.4818   1.0000
   8.750   1.3957   0.02029   0.01417  -0.1293   0.4524   1.0000
   9.000   1.3992   0.02144   0.01517  -0.1259   0.4214   1.0000
   9.250   1.3996   0.02284   0.01639  -0.1222   0.3893   1.0000
   9.500   1.3989   0.02440   0.01780  -0.1186   0.3576   1.0000
  10.250   1.3935   0.02990   0.02287  -0.1086   0.2668   1.0000
  10.500   1.3932   0.03186   0.02473  -0.1058   0.2405   1.0000
  10.750   1.3938   0.03387   0.02664  -0.1034   0.2180   1.0000
  11.000   1.3958   0.03588   0.02858  -0.1013   0.1952   1.0000
  11.500   1.3986   0.04026   0.03281  -0.0974   0.1521   1.0000
  11.750   1.3996   0.04264   0.03509  -0.0958   0.1315   1.0000
  12.000   1.4021   0.04495   0.03733  -0.0943   0.1118   1.0000
  12.250   1.4047   0.04733   0.03965  -0.0930   0.0948   1.0000
  12.500   1.4079   0.04970   0.04198  -0.0919   0.0804   1.0000
  12.750   1.4116   0.05209   0.04436  -0.0908   0.0669   1.0000
  13.000   1.4143   0.05461   0.04686  -0.0898   0.0540   1.0000
  13.250   1.4157   0.05732   0.04954  -0.0889   0.0422   1.0000
  13.500   1.4171   0.06010   0.05231  -0.0880   0.0334   1.0000
  14.000   1.4207   0.06574   0.05804  -0.0865   0.0226   1.0000
  14.250   1.4230   0.06858   0.06095  -0.0860   0.0200   1.0000
  14.500   1.4250   0.07149   0.06395  -0.0855   0.0182   1.0000
  14.750   1.4263   0.07455   0.06712  -0.0852   0.0170   1.0000
  15.000   1.4284   0.07758   0.07027  -0.0849   0.0162   1.0000
  15.250   1.4295   0.08078   0.07360  -0.0848   0.0155   1.0000
  15.500   1.4296   0.08418   0.07712  -0.0848   0.0149   1.0000
  15.750   1.4283   0.08779   0.08085  -0.0849   0.0145   1.0000
  16.250   1.4243   0.09547   0.08879  -0.0856   0.0138   1.0000
  16.500   1.4227   0.09934   0.09281  -0.0862   0.0135   1.0000
  16.750   1.4209   0.10329   0.09690  -0.0869   0.0132   1.0000
  17.000   1.4190   0.10729   0.10106  -0.0878   0.0129   1.0000
  17.250   1.4171   0.11133   0.10522  -0.0888   0.0126   1.0000
  17.500   1.4151   0.11540   0.10942  -0.0899   0.0123   1.0000
  17.750   1.4131   0.11952   0.11365  -0.0912   0.0120   1.0000
  18.000   1.4112   0.12366   0.11790  -0.0926   0.0118   1.0000
  18.250   1.4089   0.12787   0.12221  -0.0942   0.0115   1.0000
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