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EPPLER 66 AIRFOIL (e66-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 66 AIRFOIL (e66-il)
Reynolds number: 200,000
Max Cl/Cd: 91.72 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e66-il-200000.txt
Download as CSV file: xf-e66-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 66 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4222   0.10001   0.09688  -0.0331   1.0000   0.0496
  -8.000  -0.4389   0.09806   0.09500  -0.0320   1.0000   0.0497
  -7.750  -0.4568   0.09628   0.09329  -0.0302   1.0000   0.0498
  -7.500  -0.4677   0.09334   0.09040  -0.0313   0.9995   0.0499
  -7.250  -0.4598   0.08704   0.08414  -0.0326   0.9966   0.0511
  -7.000  -0.4397   0.08460   0.08167  -0.0324   0.9942   0.0528
  -6.750  -0.4220   0.08050   0.07757  -0.0373   0.9888   0.0545
  -6.500  -0.3976   0.07432   0.07135  -0.0478   0.9837   0.0575
  -6.250  -0.3718   0.05782   0.05441  -0.0759   0.9731   0.0634
  -6.000  -0.3524   0.04209   0.03801  -0.0845   0.9682   0.0368
  -5.750  -0.3225   0.03390   0.02904  -0.0906   0.9644   0.0336
  -5.500  -0.2857   0.02958   0.02404  -0.0945   0.9620   0.0346
  -5.250  -0.2467   0.02574   0.01947  -0.0976   0.9605   0.0343
  -5.000  -0.2075   0.02354   0.01678  -0.1002   0.9590   0.0358
  -4.750  -0.1807   0.02235   0.01529  -0.1000   0.9531   0.0382
  -4.500  -0.1457   0.02081   0.01367  -0.1019   0.9502   0.0438
  -4.250  -0.1068   0.02004   0.01269  -0.1040   0.9477   0.0499
  -4.000  -0.0672   0.01892   0.01156  -0.1066   0.9460   0.0609
  -3.750  -0.0420   0.01821   0.01086  -0.1064   0.9392   0.0742
  -3.500  -0.0047   0.01733   0.01010  -0.1085   0.9360   0.1060
  -3.250   0.0353   0.01674   0.00966  -0.1113   0.9336   0.1523
  -3.000   0.0652   0.01639   0.00944  -0.1120   0.9281   0.1971
  -2.750   0.0990   0.01600   0.00924  -0.1135   0.9234   0.2546
  -2.500   0.1382   0.01558   0.00901  -0.1160   0.9207   0.3213
  -2.250   0.1791   0.01516   0.00879  -0.1187   0.9187   0.3917
  -2.000   0.2026   0.01498   0.00878  -0.1180   0.9105   0.4501
  -1.750   0.2404   0.01460   0.00862  -0.1199   0.9074   0.5245
  -1.500   0.2802   0.01419   0.00841  -0.1220   0.9053   0.5989
  -1.250   0.3040   0.01405   0.00845  -0.1210   0.8976   0.6597
  -1.000   0.3386   0.01370   0.00826  -0.1218   0.8940   0.7255
  -0.750   0.3749   0.01327   0.00798  -0.1227   0.8917   0.7889
  -0.500   0.3943   0.01310   0.00792  -0.1203   0.8841   0.8464
  -0.250   0.4230   0.01268   0.00759  -0.1195   0.8798   0.9188
   0.000   0.4737   0.01226   0.00711  -0.1238   0.8778   1.0000
   0.250   0.5073   0.01215   0.00692  -0.1250   0.8713   1.0000
   0.500   0.5448   0.01195   0.00664  -0.1268   0.8658   1.0000
   0.750   0.5881   0.01163   0.00626  -0.1296   0.8625   1.0000
   1.000   0.6158   0.01161   0.00619  -0.1295   0.8532   1.0000
   1.250   0.6566   0.01133   0.00587  -0.1318   0.8484   1.0000
   1.750   0.7237   0.01107   0.00553  -0.1336   0.8325   1.0000
   2.000   0.7513   0.01104   0.00549  -0.1333   0.8214   1.0000
   2.250   0.7805   0.01099   0.00544  -0.1333   0.8106   1.0000
   2.500   0.8117   0.01092   0.00535  -0.1337   0.8000   1.0000
   2.750   0.8436   0.01085   0.00524  -0.1342   0.7889   1.0000
   3.000   0.8721   0.01084   0.00523  -0.1341   0.7760   1.0000
   3.250   0.8995   0.01087   0.00524  -0.1337   0.7619   1.0000
   3.500   0.9270   0.01090   0.00526  -0.1333   0.7470   1.0000
   3.750   0.9529   0.01098   0.00532  -0.1327   0.7305   1.0000
   4.000   0.9778   0.01107   0.00543  -0.1319   0.7125   1.0000
   4.250   1.0031   0.01118   0.00552  -0.1311   0.6933   1.0000
   4.500   1.0287   0.01132   0.00561  -0.1304   0.6736   1.0000
   4.750   1.0517   0.01150   0.00580  -0.1292   0.6511   1.0000
   5.000   1.0749   0.01172   0.00596  -0.1281   0.6277   1.0000
   5.250   1.0971   0.01198   0.00616  -0.1267   0.6021   1.0000
   5.500   1.1179   0.01227   0.00640  -0.1252   0.5738   1.0000
   5.750   1.1376   0.01263   0.00668  -0.1234   0.5430   1.0000
   6.000   1.1561   0.01303   0.00700  -0.1215   0.5095   1.0000
   6.250   1.1735   0.01351   0.00737  -0.1194   0.4741   1.0000
   6.500   1.1896   0.01406   0.00779  -0.1172   0.4368   1.0000
   6.750   1.2043   0.01468   0.00826  -0.1148   0.3984   1.0000
   7.000   1.2178   0.01537   0.00882  -0.1122   0.3576   1.0000
   7.250   1.2289   0.01619   0.00943  -0.1093   0.3131   1.0000
   7.500   1.2381   0.01708   0.01009  -0.1062   0.2689   1.0000
   7.750   1.2472   0.01801   0.01081  -0.1031   0.2276   1.0000
   8.000   1.2573   0.01898   0.01161  -0.1003   0.1914   1.0000
   8.250   1.2674   0.02001   0.01248  -0.0976   0.1590   1.0000
   8.500   1.2769   0.02112   0.01344  -0.0949   0.1301   1.0000
   8.750   1.2859   0.02231   0.01452  -0.0922   0.1044   1.0000
   9.000   1.2934   0.02365   0.01576  -0.0893   0.0825   1.0000
   9.250   1.2982   0.02522   0.01722  -0.0861   0.0653   1.0000
   9.500   1.3029   0.02684   0.01881  -0.0831   0.0534   1.0000
   9.750   1.3092   0.02841   0.02046  -0.0803   0.0463   1.0000
  10.000   1.3118   0.03035   0.02238  -0.0773   0.0415   1.0000
  10.250   1.3202   0.03196   0.02413  -0.0750   0.0379   1.0000
  10.500   1.3292   0.03344   0.02568  -0.0730   0.0344   1.0000
  10.750   1.3339   0.03572   0.02799  -0.0707   0.0319   1.0000
  11.000   1.3448   0.03774   0.03016  -0.0689   0.0299   1.0000
  11.250   1.3553   0.03940   0.03198  -0.0672   0.0278   1.0000
  11.500   1.3638   0.04114   0.03381  -0.0656   0.0258   1.0000
  11.750   1.3734   0.04345   0.03615  -0.0642   0.0242   1.0000
  12.000   1.3895   0.04694   0.03986  -0.0632   0.0229   1.0000
  12.250   1.3965   0.04940   0.04260  -0.0615   0.0223   1.0000
  12.500   1.4008   0.05220   0.04568  -0.0597   0.0216   1.0000
  12.750   1.4014   0.05510   0.04885  -0.0581   0.0208   1.0000
  13.000   1.3999   0.05804   0.05201  -0.0566   0.0201   1.0000
  13.250   1.3977   0.06103   0.05519  -0.0554   0.0194   1.0000
  13.500   1.3932   0.06426   0.05863  -0.0545   0.0188   1.0000
  13.750   1.3872   0.06795   0.06250  -0.0538   0.0184   1.0000
  14.000   1.3782   0.07227   0.06705  -0.0534   0.0182   1.0000
  14.250   1.3661   0.07709   0.07211  -0.0535   0.0181   1.0000
  14.500   1.3512   0.08245   0.07773  -0.0542   0.0180   1.0000
  14.750   1.3337   0.08840   0.08395  -0.0557   0.0180   1.0000
  15.000   1.3140   0.09504   0.09086  -0.0580   0.0181   1.0000
  15.250   1.2911   0.10279   0.09889  -0.0615   0.0183   1.0000
  15.500   1.2654   0.11172   0.10811  -0.0663   0.0186   1.0000
  15.750   1.2239   0.12517   0.12190  -0.0751   0.0194   1.0000
  16.000   1.1863   0.13962   0.13662  -0.0853   0.0202   1.0000
  16.250   1.1461   0.15707   0.15422  -0.0973   0.0218   1.0000
  16.500   1.1223   0.17040   0.16757  -0.1055   0.0229   1.0000
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