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EPPLER 668 AIRFOIL (e668-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 668 AIRFOIL (e668-il)
Reynolds number: 500,000
Max Cl/Cd: 122.96 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e668-il-500000.txt
Download as CSV file: xf-e668-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 668 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.0515   0.08640   0.08354  -0.1169   0.8763   0.0207
 -11.250  -0.0633   0.07894   0.07610  -0.1206   0.8750   0.0211
 -11.000  -0.0693   0.07316   0.07034  -0.1226   0.8738   0.0213
 -10.750  -0.0659   0.06998   0.06716  -0.1234   0.8725   0.0215
 -10.500  -0.0615   0.06718   0.06437  -0.1240   0.8711   0.0218
 -10.250  -0.0624   0.06306   0.06026  -0.1256   0.8697   0.0219
 -10.000  -0.0652   0.05874   0.05594  -0.1272   0.8681   0.0222
  -9.750  -0.0743   0.05300   0.05021  -0.1298   0.8663   0.0224
  -9.500  -0.1242   0.03828   0.03542  -0.1407   0.8643   0.0220
  -9.250  -0.2975   0.03358   0.02955  -0.1439   0.8606   0.0115
  -9.000  -0.2899   0.03169   0.02758  -0.1424   0.8587   0.0107
  -8.750  -0.3151   0.02500   0.01993  -0.1374   0.8554   0.0089
  -8.500  -0.3014   0.02324   0.01782  -0.1360   0.8536   0.0088
  -8.250  -0.2837   0.02186   0.01620  -0.1350   0.8521   0.0087
  -8.000  -0.2640   0.02073   0.01486  -0.1342   0.8506   0.0087
  -7.750  -0.2455   0.01920   0.01314  -0.1333   0.8492   0.0088
  -7.500  -0.2263   0.01788   0.01173  -0.1324   0.8476   0.0090
  -7.250  -0.2047   0.01711   0.01089  -0.1317   0.8459   0.0093
  -7.000  -0.1822   0.01645   0.01017  -0.1312   0.8442   0.0098
  -6.750  -0.1592   0.01585   0.00950  -0.1307   0.8426   0.0105
  -6.500  -0.1356   0.01529   0.00884  -0.1302   0.8411   0.0113
  -6.250  -0.1125   0.01467   0.00821  -0.1298   0.8394   0.0127
  -6.000  -0.0880   0.01415   0.00762  -0.1295   0.8378   0.0146
  -5.750  -0.0626   0.01373   0.00716  -0.1293   0.8364   0.0178
  -5.500  -0.0371   0.01342   0.00685  -0.1292   0.8350   0.0235
  -5.250  -0.0118   0.01318   0.00661  -0.1290   0.8335   0.0310
  -5.000   0.0131   0.01284   0.00635  -0.1289   0.8316   0.0415
  -4.750   0.0383   0.01250   0.00609  -0.1287   0.8296   0.0569
  -4.500   0.0640   0.01216   0.00587  -0.1287   0.8277   0.0846
  -4.250   0.0900   0.01182   0.00568  -0.1288   0.8257   0.1252
  -4.000   0.1167   0.01149   0.00552  -0.1290   0.8239   0.1749
  -3.750   0.1437   0.01116   0.00538  -0.1292   0.8222   0.2326
  -3.500   0.1711   0.01085   0.00526  -0.1296   0.8206   0.2999
  -3.250   0.1983   0.01059   0.00525  -0.1299   0.8189   0.3796
  -3.000   0.2235   0.01022   0.00520  -0.1299   0.8166   0.4689
  -2.750   0.2496   0.00990   0.00518  -0.1300   0.8140   0.5590
  -2.500   0.2762   0.00969   0.00521  -0.1299   0.8116   0.6385
  -2.250   0.3033   0.00962   0.00528  -0.1297   0.8094   0.6909
  -2.000   0.3314   0.00964   0.00534  -0.1296   0.8074   0.7260
  -1.750   0.3601   0.00971   0.00538  -0.1296   0.8055   0.7482
  -1.500   0.3892   0.00984   0.00547  -0.1298   0.8037   0.7646
  -1.250   0.4148   0.00994   0.00556  -0.1294   0.8006   0.7781
  -1.000   0.4407   0.01003   0.00567  -0.1289   0.7974   0.7886
  -0.750   0.4681   0.01008   0.00570  -0.1287   0.7946   0.7980
  -0.500   0.4966   0.01011   0.00570  -0.1287   0.7922   0.8068
  -0.250   0.5252   0.01010   0.00567  -0.1287   0.7901   0.8137
   0.000   0.5544   0.01016   0.00568  -0.1288   0.7881   0.8210
   0.250   0.5788   0.01020   0.00575  -0.1282   0.7842   0.8280
   0.500   0.6041   0.01019   0.00577  -0.1276   0.7804   0.8340
   0.750   0.6333   0.01014   0.00569  -0.1278   0.7774   0.8407
   1.000   0.6609   0.01004   0.00559  -0.1276   0.7748   0.8454
   1.250   0.6905   0.00999   0.00551  -0.1278   0.7725   0.8509
   1.500   0.7148   0.00999   0.00555  -0.1272   0.7677   0.8571
   1.750   0.7397   0.00988   0.00548  -0.1265   0.7636   0.8615
   2.000   0.7680   0.00974   0.00534  -0.1265   0.7602   0.8665
   2.250   0.7996   0.00963   0.00518  -0.1272   0.7573   0.8715
   2.500   0.8205   0.00955   0.00518  -0.1258   0.7514   0.8757
   2.750   0.8470   0.00940   0.00506  -0.1255   0.7466   0.8798
   3.000   0.8771   0.00923   0.00487  -0.1259   0.7427   0.8838
   3.250   0.9011   0.00916   0.00486  -0.1252   0.7352   0.8876
   3.500   0.9273   0.00897   0.00469  -0.1248   0.7293   0.8907
   3.750   0.9508   0.00890   0.00467  -0.1240   0.7210   0.8941
   4.000   0.9783   0.00878   0.00453  -0.1239   0.7135   0.8974
   4.250   1.0028   0.00876   0.00455  -0.1234   0.7021   0.9008
   4.500   1.0264   0.00871   0.00451  -0.1226   0.6898   0.9038
   4.750   1.0487   0.00870   0.00449  -0.1215   0.6751   0.9070
   5.000   1.0707   0.00875   0.00451  -0.1204   0.6581   0.9105
   5.250   1.0919   0.00888   0.00458  -0.1191   0.6379   0.9142
   5.500   1.1103   0.00906   0.00470  -0.1174   0.6132   0.9177
   5.750   1.1241   0.00930   0.00484  -0.1147   0.5874   0.9220
   6.000   1.1354   0.00963   0.00507  -0.1116   0.5598   0.9271
   6.250   1.1428   0.00996   0.00531  -0.1077   0.5333   0.9327
   6.500   1.1484   0.01033   0.00561  -0.1035   0.5078   0.9396
   6.750   1.1534   0.01079   0.00598  -0.0994   0.4831   0.9479
   7.000   1.1599   0.01122   0.00637  -0.0957   0.4587   0.9590
   7.250   1.1726   0.01179   0.00686  -0.0936   0.4309   0.9951
   7.500   1.1849   0.01254   0.00750  -0.0917   0.4035   1.0000
   7.750   1.1968   0.01335   0.00819  -0.0899   0.3758   1.0000
   8.000   1.2088   0.01419   0.00892  -0.0881   0.3480   1.0000
   8.250   1.2201   0.01510   0.00971  -0.0862   0.3207   1.0000
   8.500   1.2313   0.01604   0.01053  -0.0844   0.2950   1.0000
   8.750   1.2433   0.01695   0.01134  -0.0828   0.2696   1.0000
   9.000   1.2546   0.01793   0.01220  -0.0810   0.2446   1.0000
   9.250   1.2648   0.01898   0.01313  -0.0792   0.2201   1.0000
   9.500   1.2763   0.01997   0.01402  -0.0776   0.1961   1.0000
   9.750   1.2867   0.02105   0.01499  -0.0759   0.1752   1.0000
  10.000   1.2986   0.02205   0.01592  -0.0744   0.1556   1.0000
  10.250   1.3096   0.02313   0.01691  -0.0728   0.1377   1.0000
  10.500   1.3202   0.02424   0.01795  -0.0712   0.1212   1.0000
  10.750   1.3303   0.02541   0.01905  -0.0697   0.1061   1.0000
  11.000   1.3408   0.02657   0.02017  -0.0682   0.0932   1.0000
  11.250   1.3511   0.02777   0.02133  -0.0667   0.0814   1.0000
  11.500   1.3609   0.02903   0.02256  -0.0653   0.0710   1.0000
  11.750   1.3710   0.03029   0.02382  -0.0639   0.0620   1.0000
  12.000   1.3802   0.03164   0.02517  -0.0625   0.0542   1.0000
  12.250   1.3885   0.03310   0.02662  -0.0611   0.0475   1.0000
  12.500   1.3946   0.03478   0.02828  -0.0596   0.0415   1.0000
  12.750   1.4044   0.03617   0.02972  -0.0584   0.0370   1.0000
  13.000   1.4114   0.03786   0.03144  -0.0572   0.0329   1.0000
  13.250   1.4183   0.03960   0.03320  -0.0560   0.0298   1.0000
  13.500   1.4244   0.04145   0.03512  -0.0548   0.0271   1.0000
  13.750   1.4315   0.04325   0.03696  -0.0539   0.0247   1.0000
  14.000   1.4362   0.04533   0.03910  -0.0529   0.0226   1.0000
  14.250   1.4436   0.04720   0.04104  -0.0521   0.0207   1.0000
  14.500   1.4450   0.04976   0.04363  -0.0512   0.0191   1.0000
  14.750   1.4519   0.05178   0.04578  -0.0507   0.0178   1.0000
  15.000   1.4575   0.05398   0.04802  -0.0502   0.0162   1.0000
  15.250   1.4580   0.05684   0.05097  -0.0497   0.0152   1.0000
  15.500   1.4621   0.05938   0.05362  -0.0494   0.0142   1.0000
  15.750   1.4651   0.06210   0.05642  -0.0492   0.0131   1.0000
  16.000   1.4614   0.06574   0.06014  -0.0491   0.0123   1.0000
  16.250   1.4636   0.06873   0.06326  -0.0492   0.0114   1.0000
  16.500   1.4638   0.07204   0.06667  -0.0495   0.0106   1.0000
  16.750   1.4554   0.07668   0.07140  -0.0501   0.0099   1.0000
  17.000   1.4552   0.08026   0.07512  -0.0507   0.0092   1.0000
  17.250   1.4528   0.08424   0.07922  -0.0516   0.0085   1.0000
  17.500   1.4469   0.08886   0.08394  -0.0528   0.0079   1.0000
  17.750   1.4336   0.09481   0.09000  -0.0546   0.0076   1.0000
  18.000   1.4303   0.09928   0.09464  -0.0561   0.0071   1.0000
  18.250   1.4249   0.10416   0.09964  -0.0579   0.0065   1.0000
  18.500   1.4172   0.10952   0.10513  -0.0600   0.0063   1.0000
  18.750   1.4079   0.11526   0.11098  -0.0625   0.0060   1.0000
  19.000   1.3945   0.12183   0.11767  -0.0656   0.0058   1.0000
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