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EPPLER 67 AIRFOIL (e67-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 67 AIRFOIL (e67-il)
Reynolds number: 500,000
Max Cl/Cd: 121.31 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e67-il-500000.txt
Download as CSV file: xf-e67-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 67 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.2621   0.09117   0.08907  -0.0581   0.9895   0.0262
 -10.000  -0.2579   0.08621   0.08412  -0.0610   0.9879   0.0272
  -9.750  -0.4504   0.07252   0.07041  -0.0626   0.9934   0.0177
  -9.500  -0.4404   0.06912   0.06704  -0.0674   0.9899   0.0183
  -9.250  -0.5252   0.03246   0.02893  -0.1081   0.9714   0.0135
  -9.000  -0.5181   0.02852   0.02454  -0.1083   0.9635   0.0134
  -8.750  -0.4924   0.02587   0.02159  -0.1105   0.9611   0.0137
  -8.500  -0.4629   0.02367   0.01910  -0.1127   0.9595   0.0140
  -8.250  -0.4393   0.02208   0.01730  -0.1131   0.9557   0.0143
  -8.000  -0.4149   0.02052   0.01552  -0.1134   0.9514   0.0145
  -7.750  -0.3842   0.01902   0.01382  -0.1148   0.9493   0.0149
  -7.500  -0.3510   0.01794   0.01260  -0.1165   0.9479   0.0156
  -7.250  -0.3164   0.01692   0.01145  -0.1184   0.9469   0.0164
  -7.000  -0.2809   0.01593   0.01030  -0.1204   0.9460   0.0169
  -6.750  -0.2551   0.01495   0.00921  -0.1203   0.9419   0.0174
  -6.500  -0.2276   0.01366   0.00782  -0.1208   0.9381   0.0188
  -6.250  -0.1939   0.01299   0.00709  -0.1223   0.9361   0.0205
  -6.000  -0.1593   0.01239   0.00641  -0.1239   0.9343   0.0225
  -5.750  -0.1243   0.01159   0.00556  -0.1257   0.9326   0.0281
  -5.500  -0.0956   0.01100   0.00501  -0.1260   0.9286   0.0434
  -5.250  -0.0675   0.01057   0.00464  -0.1262   0.9238   0.0600
  -5.000  -0.0343   0.01020   0.00427  -0.1275   0.9208   0.0764
  -4.750  -0.0001   0.00980   0.00393  -0.1290   0.9182   0.0966
  -4.500   0.0261   0.00953   0.00372  -0.1288   0.9124   0.1201
  -4.250   0.0561   0.00919   0.00349  -0.1294   0.9077   0.1526
  -4.000   0.0885   0.00887   0.00324  -0.1305   0.9041   0.1867
  -3.750   0.1150   0.00864   0.00309  -0.1303   0.8979   0.2183
  -3.500   0.1444   0.00839   0.00292  -0.1307   0.8926   0.2531
  -3.250   0.1753   0.00815   0.00275  -0.1315   0.8881   0.2912
  -3.000   0.2012   0.00796   0.00266  -0.1311   0.8810   0.3304
  -2.750   0.2313   0.00775   0.00253  -0.1317   0.8759   0.3733
  -2.500   0.2580   0.00760   0.00247  -0.1315   0.8691   0.4131
  -2.250   0.2866   0.00744   0.00239  -0.1316   0.8629   0.4527
  -2.000   0.3144   0.00732   0.00234  -0.1316   0.8564   0.4898
  -1.750   0.3420   0.00721   0.00229  -0.1315   0.8496   0.5251
  -1.500   0.3703   0.00712   0.00226  -0.1316   0.8431   0.5600
  -1.250   0.3973   0.00704   0.00224  -0.1313   0.8357   0.5924
  -1.000   0.4252   0.00698   0.00223  -0.1313   0.8289   0.6238
  -0.750   0.4520   0.00692   0.00222  -0.1309   0.8210   0.6536
  -0.500   0.4793   0.00688   0.00223  -0.1307   0.8135   0.6823
  -0.250   0.5063   0.00685   0.00223  -0.1304   0.8054   0.7098
   0.000   0.5325   0.00682   0.00226  -0.1299   0.7969   0.7358
   0.250   0.5597   0.00681   0.00226  -0.1296   0.7890   0.7613
   0.500   0.5848   0.00680   0.00231  -0.1289   0.7795   0.7860
   0.750   0.6107   0.00681   0.00234  -0.1283   0.7707   0.8101
   1.000   0.6359   0.00682   0.00238  -0.1276   0.7614   0.8332
   1.250   0.6600   0.00683   0.00243  -0.1266   0.7512   0.8565
   1.500   0.6833   0.00685   0.00247  -0.1254   0.7413   0.8792
   1.750   0.7059   0.00688   0.00250  -0.1240   0.7310   0.9027
   2.000   0.7261   0.00687   0.00253  -0.1221   0.7195   0.9292
   2.250   0.7499   0.00686   0.00253  -0.1210   0.7080   0.9601
   2.500   0.7862   0.00689   0.00254  -0.1229   0.6954   1.0000
   2.750   0.8127   0.00701   0.00261  -0.1227   0.6827   1.0000
   3.000   0.8388   0.00713   0.00268  -0.1224   0.6693   1.0000
   3.250   0.8644   0.00727   0.00276  -0.1220   0.6552   1.0000
   3.500   0.8897   0.00741   0.00286  -0.1215   0.6402   1.0000
   3.750   0.9145   0.00757   0.00298  -0.1209   0.6242   1.0000
   4.000   0.9389   0.00774   0.00310  -0.1203   0.6072   1.0000
   4.250   0.9628   0.00794   0.00324  -0.1195   0.5894   1.0000
   4.500   0.9862   0.00815   0.00339  -0.1186   0.5707   1.0000
   4.750   1.0093   0.00837   0.00357  -0.1177   0.5500   1.0000
   5.000   1.0313   0.00864   0.00376  -0.1166   0.5279   1.0000
   5.250   1.0531   0.00892   0.00397  -0.1155   0.5038   1.0000
   5.500   1.0740   0.00924   0.00420  -0.1142   0.4779   1.0000
   5.750   1.0937   0.00961   0.00448  -0.1127   0.4485   1.0000
   6.000   1.1130   0.01001   0.00476  -0.1111   0.4192   1.0000
   6.250   1.1317   0.01045   0.00508  -0.1095   0.3887   1.0000
   6.500   1.1487   0.01097   0.00545  -0.1076   0.3547   1.0000
   6.750   1.1645   0.01152   0.00584  -0.1055   0.3174   1.0000
   7.000   1.1779   0.01217   0.00629  -0.1030   0.2773   1.0000
   7.250   1.1907   0.01288   0.00679  -0.1005   0.2386   1.0000
   7.500   1.2055   0.01352   0.00728  -0.0983   0.2077   1.0000
   7.750   1.2201   0.01417   0.00780  -0.0962   0.1801   1.0000
   8.000   1.2342   0.01485   0.00835  -0.0940   0.1539   1.0000
   8.250   1.2481   0.01557   0.00894  -0.0918   0.1298   1.0000
   8.500   1.2624   0.01625   0.00954  -0.0898   0.1095   1.0000
   8.750   1.2759   0.01699   0.01021  -0.0876   0.0915   1.0000
   9.000   1.2891   0.01775   0.01090  -0.0855   0.0757   1.0000
   9.250   1.3019   0.01855   0.01164  -0.0833   0.0610   1.0000
   9.500   1.3131   0.01945   0.01247  -0.0810   0.0471   1.0000
   9.750   1.3225   0.02050   0.01344  -0.0785   0.0353   1.0000
  10.000   1.3325   0.02152   0.01445  -0.0761   0.0280   1.0000
  10.250   1.3416   0.02263   0.01559  -0.0737   0.0235   1.0000
  10.500   1.3526   0.02362   0.01665  -0.0716   0.0207   1.0000
  10.750   1.3559   0.02519   0.01827  -0.0687   0.0182   1.0000
  11.000   1.3674   0.02619   0.01937  -0.0669   0.0170   1.0000
  11.250   1.3777   0.02731   0.02056  -0.0651   0.0158   1.0000
  11.500   1.3861   0.02859   0.02189  -0.0632   0.0145   1.0000
  11.750   1.3841   0.03075   0.02414  -0.0604   0.0132   1.0000
  12.000   1.3909   0.03227   0.02576  -0.0587   0.0126   1.0000
  12.250   1.3984   0.03377   0.02736  -0.0571   0.0119   1.0000
  12.500   1.4041   0.03548   0.02916  -0.0555   0.0112   1.0000
  12.750   1.4080   0.03740   0.03117  -0.0539   0.0108   1.0000
  13.000   1.4107   0.03950   0.03336  -0.0525   0.0103   1.0000
  13.250   1.4070   0.04232   0.03628  -0.0509   0.0098   1.0000
  13.500   1.3976   0.04592   0.04002  -0.0493   0.0095   1.0000
  13.750   1.4003   0.04837   0.04259  -0.0485   0.0092   1.0000
  14.000   1.4021   0.05098   0.04533  -0.0478   0.0090   1.0000
  14.250   1.4032   0.05377   0.04826  -0.0472   0.0088   1.0000
  14.500   1.4031   0.05681   0.05142  -0.0469   0.0085   1.0000
  14.750   1.4024   0.06003   0.05477  -0.0467   0.0083   1.0000
  15.000   1.4010   0.06343   0.05831  -0.0467   0.0081   1.0000
  15.250   1.3986   0.06709   0.06210  -0.0469   0.0080   1.0000
  15.500   1.3959   0.07091   0.06605  -0.0474   0.0079   1.0000
  15.750   1.3926   0.07494   0.07021  -0.0482   0.0077   1.0000
  16.000   1.3881   0.07924   0.07465  -0.0491   0.0075   1.0000
  16.250   1.3831   0.08378   0.07931  -0.0504   0.0074   1.0000
  16.500   1.3774   0.08854   0.08422  -0.0519   0.0073   1.0000
  16.750   1.3707   0.09362   0.08944  -0.0537   0.0072   1.0000
  17.000   1.3630   0.09896   0.09492  -0.0558   0.0071   1.0000
  17.250   1.3543   0.10466   0.10077  -0.0582   0.0071   1.0000
  17.500   1.3449   0.11063   0.10690  -0.0609   0.0071   1.0000
  17.750   1.3349   0.11687   0.11329  -0.0640   0.0070   1.0000
  18.000   1.3240   0.12344   0.12002  -0.0675   0.0070   1.0000
  18.250   1.3125   0.13030   0.12704  -0.0713   0.0070   1.0000
  18.500   1.3006   0.13747   0.13438  -0.0756   0.0070   1.0000
  18.750   1.2879   0.14501   0.14208  -0.0802   0.0070   1.0000
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