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EPPLER 668 AIRFOIL (e668-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 668 AIRFOIL (e668-il)
Reynolds number: 1,000,000
Max Cl/Cd: 155.47 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e668-il-1000000.txt
Download as CSV file: xf-e668-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.1154   0.08507   0.08247  -0.1273   0.8409   0.0112
 -11.250  -0.1282   0.07875   0.07617  -0.1299   0.8396   0.0114
 -11.000  -0.1296   0.07492   0.07236  -0.1317   0.8384   0.0115
 -10.750  -0.1358   0.06971   0.06715  -0.1342   0.8369   0.0115
 -10.500  -0.3342   0.03400   0.03069  -0.1496   0.8316   0.0066
 -10.250  -0.3322   0.03251   0.02922  -0.1483   0.8302   0.0063
 -10.000  -0.3643   0.02951   0.02603  -0.1434   0.8277   0.0061
  -9.750  -0.3795   0.02650   0.02272  -0.1398   0.8256   0.0058
  -9.500  -0.3841   0.02350   0.01935  -0.1369   0.8239   0.0055
  -9.250  -0.3883   0.01957   0.01482  -0.1335   0.8222   0.0050
  -9.000  -0.3728   0.01811   0.01312  -0.1322   0.8208   0.0049
  -8.750  -0.3537   0.01713   0.01198  -0.1314   0.8191   0.0049
  -8.500  -0.3339   0.01613   0.01085  -0.1306   0.8183   0.0049
  -8.250  -0.3123   0.01533   0.00995  -0.1300   0.8174   0.0049
  -8.000  -0.2898   0.01462   0.00915  -0.1295   0.8165   0.0049
  -7.750  -0.2669   0.01395   0.00840  -0.1291   0.8153   0.0050
  -7.500  -0.2433   0.01334   0.00772  -0.1287   0.8141   0.0052
  -7.250  -0.2186   0.01284   0.00716  -0.1285   0.8128   0.0053
  -7.000  -0.1936   0.01237   0.00664  -0.1283   0.8117   0.0055
  -6.750  -0.1679   0.01194   0.00615  -0.1282   0.8105   0.0057
  -6.500  -0.1418   0.01156   0.00571  -0.1282   0.8094   0.0060
  -6.250  -0.1156   0.01115   0.00524  -0.1281   0.8082   0.0067
  -6.000  -0.0890   0.01080   0.00485  -0.1282   0.8070   0.0079
  -5.750  -0.0620   0.01049   0.00452  -0.1282   0.8058   0.0107
  -5.500  -0.0350   0.01023   0.00427  -0.1283   0.8046   0.0160
  -5.250  -0.0077   0.01008   0.00413  -0.1285   0.8032   0.0210
  -5.000   0.0197   0.00983   0.00392  -0.1286   0.8022   0.0273
  -4.750   0.0472   0.00961   0.00374  -0.1288   0.8011   0.0357
  -4.500   0.0746   0.00937   0.00356  -0.1290   0.7997   0.0498
  -4.250   0.1021   0.00911   0.00340  -0.1292   0.7982   0.0719
  -4.000   0.1296   0.00881   0.00325  -0.1295   0.7966   0.1070
  -3.750   0.1572   0.00849   0.00310  -0.1298   0.7949   0.1524
  -3.500   0.1853   0.00821   0.00296  -0.1302   0.7933   0.1988
  -3.250   0.2136   0.00795   0.00285  -0.1307   0.7918   0.2481
  -3.000   0.2421   0.00770   0.00274  -0.1311   0.7903   0.3046
  -2.750   0.2704   0.00745   0.00271  -0.1316   0.7884   0.3774
  -2.500   0.2984   0.00717   0.00265  -0.1320   0.7867   0.4500
  -2.250   0.3266   0.00685   0.00256  -0.1324   0.7848   0.5254
  -2.000   0.3551   0.00658   0.00250  -0.1328   0.7827   0.5963
  -1.750   0.3838   0.00639   0.00246  -0.1332   0.7805   0.6533
  -1.500   0.4126   0.00628   0.00245  -0.1334   0.7785   0.6950
  -1.250   0.4417   0.00624   0.00244  -0.1337   0.7765   0.7223
  -1.000   0.4711   0.00623   0.00243  -0.1341   0.7745   0.7412
  -0.750   0.5002   0.00629   0.00248  -0.1344   0.7721   0.7545
  -0.500   0.5284   0.00627   0.00248  -0.1345   0.7698   0.7657
  -0.250   0.5570   0.00626   0.00247  -0.1347   0.7670   0.7750
   0.000   0.5856   0.00624   0.00245  -0.1349   0.7641   0.7817
   0.250   0.6146   0.00622   0.00243  -0.1351   0.7614   0.7883
   0.500   0.6439   0.00622   0.00240  -0.1355   0.7588   0.7947
   0.750   0.6720   0.00623   0.00243  -0.1355   0.7558   0.7999
   1.000   0.6998   0.00622   0.00244  -0.1356   0.7520   0.8053
   1.250   0.7284   0.00620   0.00242  -0.1358   0.7481   0.8100
   1.500   0.7564   0.00616   0.00238  -0.1359   0.7444   0.8141
   1.750   0.7841   0.00617   0.00241  -0.1359   0.7401   0.8185
   2.000   0.8118   0.00617   0.00243  -0.1359   0.7346   0.8231
   2.250   0.8397   0.00615   0.00239  -0.1360   0.7291   0.8270
   2.500   0.8665   0.00615   0.00243  -0.1359   0.7221   0.8305
   2.750   0.8934   0.00616   0.00244  -0.1357   0.7146   0.8343
   3.000   0.9203   0.00620   0.00248  -0.1356   0.7054   0.8382
   3.250   0.9470   0.00626   0.00252  -0.1355   0.6951   0.8413
   3.500   0.9721   0.00631   0.00255  -0.1350   0.6821   0.8442
   3.750   0.9964   0.00641   0.00262  -0.1344   0.6659   0.8470
   4.000   1.0199   0.00656   0.00272  -0.1336   0.6468   0.8497
   4.250   1.0416   0.00678   0.00285  -0.1325   0.6241   0.8525
   4.500   1.0624   0.00705   0.00302  -0.1312   0.5977   0.8551
   4.750   1.0812   0.00735   0.00321  -0.1296   0.5700   0.8575
   5.000   1.0978   0.00770   0.00345  -0.1275   0.5408   0.8602
   5.250   1.1133   0.00807   0.00371  -0.1253   0.5116   0.8629
   5.500   1.1277   0.00847   0.00400  -0.1228   0.4832   0.8658
   5.750   1.1414   0.00883   0.00426  -0.1203   0.4568   0.8688
   6.000   1.1528   0.00921   0.00455  -0.1172   0.4329   0.8716
   6.250   1.1623   0.00965   0.00489  -0.1139   0.4061   0.8751
   6.500   1.1736   0.01009   0.00525  -0.1110   0.3814   0.8785
   6.750   1.1842   0.01060   0.00566  -0.1081   0.3575   0.8820
   7.000   1.1955   0.01113   0.00610  -0.1053   0.3319   0.8855
   7.250   1.2059   0.01170   0.00657  -0.1026   0.3075   0.8889
   7.500   1.2154   0.01233   0.00710  -0.0997   0.2825   0.8929
   7.750   1.2271   0.01293   0.00763  -0.0974   0.2612   0.8970
   8.000   1.2378   0.01363   0.00824  -0.0950   0.2377   0.9011
   8.250   1.2482   0.01433   0.00886  -0.0925   0.2152   0.9057
   8.500   1.2581   0.01509   0.00953  -0.0901   0.1928   0.9114
   8.750   1.2696   0.01584   0.01020  -0.0880   0.1730   0.9172
   9.000   1.2811   0.01652   0.01086  -0.0859   0.1565   0.9250
   9.250   1.2916   0.01723   0.01154  -0.0837   0.1404   0.9373
   9.500   1.3044   0.01795   0.01225  -0.0821   0.1236   1.0000
   9.750   1.3183   0.01881   0.01303  -0.0807   0.1094   1.0000
  10.000   1.3323   0.01966   0.01383  -0.0794   0.0967   1.0000
  10.250   1.3458   0.02054   0.01466  -0.0780   0.0851   1.0000
  10.500   1.3590   0.02144   0.01551  -0.0767   0.0744   1.0000
  10.750   1.3714   0.02240   0.01642  -0.0753   0.0644   1.0000
  11.000   1.3843   0.02334   0.01734  -0.0739   0.0566   1.0000
  11.250   1.3958   0.02437   0.01833  -0.0724   0.0482   1.0000
  11.500   1.4068   0.02546   0.01939  -0.0710   0.0413   1.0000
  11.750   1.4178   0.02657   0.02046  -0.0695   0.0346   1.0000
  12.000   1.4296   0.02764   0.02153  -0.0682   0.0302   1.0000
  12.250   1.4408   0.02876   0.02266  -0.0669   0.0262   1.0000
  12.500   1.4515   0.02995   0.02385  -0.0656   0.0230   1.0000
  12.750   1.4625   0.03113   0.02506  -0.0644   0.0208   1.0000
  13.000   1.4731   0.03238   0.02634  -0.0632   0.0186   1.0000
  13.250   1.4836   0.03365   0.02765  -0.0620   0.0169   1.0000
  13.500   1.4923   0.03510   0.02912  -0.0608   0.0154   1.0000
  13.750   1.5035   0.03638   0.03046  -0.0598   0.0143   1.0000
  14.000   1.5119   0.03792   0.03203  -0.0587   0.0130   1.0000
  14.250   1.5210   0.03945   0.03362  -0.0577   0.0120   1.0000
  14.500   1.5299   0.04100   0.03523  -0.0568   0.0111   1.0000
  14.750   1.5363   0.04285   0.03711  -0.0558   0.0101   1.0000
  15.000   1.5447   0.04453   0.03886  -0.0551   0.0092   1.0000
  15.250   1.5516   0.04640   0.04079  -0.0543   0.0084   1.0000
  15.500   1.5555   0.04866   0.04309  -0.0535   0.0076   1.0000
  15.750   1.5633   0.05052   0.04504  -0.0529   0.0068   1.0000
  16.000   1.5670   0.05288   0.04745  -0.0523   0.0059   1.0000
  16.250   1.5712   0.05527   0.04992  -0.0519   0.0053   1.0000
  16.500   1.5746   0.05780   0.05251  -0.0515   0.0047   1.0000
  16.750   1.5747   0.06080   0.05558  -0.0512   0.0039   1.0000
  17.000   1.5762   0.06371   0.05858  -0.0511   0.0035   1.0000
  17.250   1.5744   0.06709   0.06204  -0.0512   0.0031   1.0000
  17.500   1.5707   0.07089   0.06595  -0.0514   0.0026   1.0000
  17.750   1.5695   0.07441   0.06958  -0.0518   0.0025   1.0000
  18.000   1.5666   0.07830   0.07357  -0.0524   0.0023   1.0000
  18.250   1.5598   0.08285   0.07823  -0.0533   0.0021   1.0000
  18.500   1.5542   0.08732   0.08282  -0.0544   0.0020   1.0000
  18.750   1.5439   0.09270   0.08833  -0.0560   0.0019   1.0000
  19.000   1.5314   0.09859   0.09436  -0.0579   0.0018   1.0000
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