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GOE 8K AIRFOIL (goe08k-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 8K AIRFOIL (goe08k-il)
Reynolds number: 500,000
Max Cl/Cd: 103.53 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe08k-il-500000.txt
Download as CSV file: xf-goe08k-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 8K 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000   0.0462   0.08976   0.08690  -0.1786   0.9309   0.0306
 -10.750   0.0253   0.08911   0.08628  -0.1720   0.9222   0.0306
 -10.500   0.0310   0.08438   0.08156  -0.1760   0.9213   0.0307
 -10.000   0.0519   0.07720   0.07436  -0.1800   0.9201   0.0316
  -9.750   0.0687   0.07488   0.07202  -0.1822   0.9196   0.0324
  -9.500   0.0777   0.07027   0.06740  -0.1871   0.9189   0.0325
  -9.250  -0.0238   0.05360   0.05072  -0.1931   0.9067   0.0252
  -9.000  -0.0578   0.05208   0.04918  -0.1856   0.8990   0.0250
  -8.750  -0.0855   0.04690   0.04384  -0.1822   0.8935   0.0248
  -8.500  -0.1183   0.03718   0.03361  -0.1798   0.8907   0.0246
  -8.250  -0.1558   0.03829   0.03476  -0.1664   0.8798   0.0246
  -8.000  -0.2289   0.03153   0.02738  -0.1498   0.8695   0.0251
  -7.750  -0.2474   0.02688   0.02215  -0.1426   0.8654   0.0262
  -7.500  -0.2115   0.02746   0.02280  -0.1446   0.8649   0.0268
  -7.250  -0.1838   0.02676   0.02200  -0.1453   0.8641   0.0275
  -7.000  -0.1663   0.02436   0.01923  -0.1440   0.8631   0.0292
  -6.750  -0.1962   0.02427   0.01902  -0.1321   0.8534   0.0294
  -6.500  -0.1841   0.02191   0.01619  -0.1293   0.8516   0.0313
  -6.250  -0.1558   0.02145   0.01568  -0.1298   0.8507   0.0320
  -6.000  -0.1245   0.02132   0.01554  -0.1309   0.8499   0.0332
  -5.750  -0.0940   0.02077   0.01484  -0.1318   0.8492   0.0355
  -5.500  -0.0658   0.01944   0.01323  -0.1321   0.8486   0.0377
  -5.250  -0.0938   0.01999   0.01375  -0.1204   0.8391   0.0379
  -5.000  -0.0660   0.01993   0.01372  -0.1208   0.8378   0.0392
  -4.750  -0.0366   0.01956   0.01330  -0.1214   0.8367   0.0412
  -4.500  -0.0063   0.01906   0.01262  -0.1219   0.8359   0.0437
  -4.250   0.0244   0.01791   0.01133  -0.1229   0.8352   0.0459
  -4.000   0.0583   0.01742   0.01083  -0.1246   0.8346   0.0478
  -3.750   0.0934   0.01706   0.01042  -0.1265   0.8340   0.0509
  -3.500   0.0590   0.01782   0.01117  -0.1132   0.8244   0.0508
  -3.250   0.0869   0.01761   0.01085  -0.1134   0.8231   0.0528
  -3.000   0.1180   0.01672   0.00987  -0.1143   0.8223   0.0551
  -2.750   0.1499   0.01607   0.00924  -0.1155   0.8216   0.0571
  -2.500   0.1828   0.01565   0.00881  -0.1169   0.8209   0.0595
  -2.250   0.2176   0.01522   0.00834  -0.1187   0.8203   0.0618
  -2.000   0.2536   0.01482   0.00790  -0.1207   0.8197   0.0633
  -1.750   0.2155   0.01568   0.00876  -0.1066   0.8102   0.0633
  -1.500   0.2431   0.01552   0.00856  -0.1068   0.8088   0.0646
  -1.250   0.2718   0.01500   0.00803  -0.1072   0.8079   0.0660
  -1.000   0.3008   0.01452   0.00754  -0.1076   0.8070   0.0677
  -0.750   0.3327   0.01417   0.00719  -0.1088   0.8063   0.0694
  -0.500   0.3665   0.01388   0.00690  -0.1103   0.8057   0.0721
  -0.250   0.4015   0.01361   0.00662  -0.1121   0.8051   0.0743
   0.000   0.4375   0.01339   0.00638  -0.1142   0.8046   0.0759
   0.250   0.4753   0.01321   0.00619  -0.1167   0.8040   0.0780
   0.750   0.6778   0.01103   0.00667  -0.1528   0.8065   0.9043
   1.000   0.6289   0.01144   0.00704  -0.1357   0.8001   0.8900
   1.250   0.4672   0.01490   0.00791  -0.0922   0.7858   0.0888
   1.500   0.5207   0.01369   0.00751  -0.0984   0.7867   0.3635
   1.750   0.9611   0.01142   0.00698  -0.1931   0.8063   1.0000
   2.000   1.0039   0.01128   0.00680  -0.1969   0.8050   1.0000
   2.250   0.9648   0.01181   0.00737  -0.1823   0.7979   1.0000
   2.500   0.9829   0.01187   0.00742  -0.1805   0.7950   1.0000
   2.750   1.0160   0.01176   0.00731  -0.1820   0.7932   1.0000
   3.000   1.0543   0.01163   0.00717  -0.1847   0.7917   1.0000
   3.250   1.0958   0.01152   0.00706  -0.1881   0.7904   1.0000
   3.500   1.0584   0.01213   0.00771  -0.1739   0.7829   1.0000
   3.750   1.0823   0.01214   0.00774  -0.1734   0.7803   1.0000
   4.000   1.1192   0.01197   0.00758  -0.1757   0.7782   1.0000
   4.250   1.1767   0.01152   0.00711  -0.1825   0.7753   1.0000
   4.500   1.1415   0.01207   0.00771  -0.1687   0.7670   1.0000
   4.750   1.1789   0.01181   0.00743  -0.1710   0.7632   1.0000
   5.000   1.1942   0.01187   0.00751  -0.1684   0.7579   1.0000
   5.250   1.1967   0.01206   0.00773  -0.1631   0.7511   1.0000
   5.500   1.2268   0.01185   0.00751  -0.1637   0.7444   1.0000
   5.750   1.2206   0.01216   0.00784  -0.1565   0.7353   1.0000
   6.000   1.2261   0.01233   0.00802  -0.1518   0.7253   1.0000
   6.250   1.2459   0.01231   0.00797  -0.1502   0.7156   1.0000
   6.500   1.2388   0.01281   0.00850  -0.1431   0.7039   1.0000
   6.750   1.2427   0.01323   0.00897  -0.1384   0.6943   1.0000
   7.000   1.2493   0.01361   0.00935  -0.1343   0.6816   1.0000
   7.250   1.2505   0.01417   0.00991  -0.1291   0.6654   1.0000
   7.500   1.2509   0.01481   0.01053  -0.1239   0.6442   1.0000
   7.750   1.2451   0.01572   0.01131  -0.1176   0.6071   1.0000
   8.000   1.2363   0.01688   0.01226  -0.1110   0.5660   1.0000
   8.250   1.2233   0.01835   0.01351  -0.1038   0.5247   1.0000
   8.500   1.2114   0.01996   0.01489  -0.0972   0.4857   1.0000
   8.750   1.2037   0.02150   0.01626  -0.0915   0.4484   1.0000
   9.000   1.1964   0.02312   0.01770  -0.0862   0.4101   1.0000
   9.250   1.1859   0.02501   0.01934  -0.0805   0.3603   1.0000
   9.500   1.1755   0.02700   0.02104  -0.0752   0.3050   1.0000
   9.750   1.1659   0.02904   0.02275  -0.0701   0.2478   1.0000
  10.000   1.1622   0.03081   0.02427  -0.0661   0.2022   1.0000
  10.250   1.1590   0.03261   0.02579  -0.0623   0.1529   1.0000
  10.500   1.1521   0.03470   0.02750  -0.0582   0.0922   1.0000
  10.750   1.1539   0.03629   0.02894  -0.0553   0.0667   1.0000
  11.000   1.1590   0.03773   0.03030  -0.0528   0.0499   1.0000
  11.250   1.1659   0.03906   0.03158  -0.0506   0.0404   1.0000
  11.500   1.1751   0.04024   0.03277  -0.0488   0.0363   1.0000
  11.750   1.1824   0.04159   0.03415  -0.0467   0.0332   1.0000
  12.000   1.1925   0.04274   0.03535  -0.0451   0.0310   1.0000
  12.250   1.1990   0.04418   0.03681  -0.0432   0.0287   1.0000
  12.500   1.2021   0.04593   0.03862  -0.0408   0.0272   1.0000
  12.750   1.2116   0.04720   0.03997  -0.0393   0.0259   1.0000
  13.000   1.2202   0.04854   0.04135  -0.0378   0.0243   1.0000
  13.250   1.2264   0.05009   0.04295  -0.0360   0.0233   1.0000
  13.500   1.2280   0.05206   0.04497  -0.0339   0.0225   1.0000
  13.750   1.2288   0.05411   0.04710  -0.0317   0.0217   1.0000
  14.000   1.2368   0.05560   0.04866  -0.0304   0.0212   1.0000
  14.250   1.2436   0.05719   0.05034  -0.0289   0.0207   1.0000
  14.500   1.2485   0.05897   0.05220  -0.0273   0.0200   1.0000
  14.750   1.2552   0.06062   0.05390  -0.0260   0.0191   1.0000
  15.000   1.2609   0.06235   0.05566  -0.0248   0.0184   1.0000
  15.250   1.2631   0.06439   0.05775  -0.0232   0.0179   1.0000
  15.500   1.2647   0.06640   0.05983  -0.0214   0.0173   1.0000
  15.750   1.2721   0.06808   0.06161  -0.0204   0.0169   1.0000
  16.000   1.2783   0.06985   0.06348  -0.0193   0.0164   1.0000
  16.250   1.2843   0.07158   0.06530  -0.0181   0.0161   1.0000
  16.500   1.2896   0.07345   0.06726  -0.0171   0.0156   1.0000
  16.750   1.2947   0.07536   0.06925  -0.0161   0.0152   1.0000
  17.000   1.2999   0.07725   0.07121  -0.0151   0.0149   1.0000
  17.250   1.3040   0.07927   0.07330  -0.0143   0.0146   1.0000
  17.500   1.3084   0.08119   0.07524  -0.0134   0.0141   1.0000
  17.750   1.3147   0.08273   0.07685  -0.0121   0.0137   1.0000
  18.000   1.3180   0.08490   0.07918  -0.0111   0.0136   1.0000
  18.250   1.3158   0.08796   0.08240  -0.0108   0.0133   1.0000
  18.500   1.3170   0.09041   0.08502  -0.0098   0.0132   1.0000
  18.750   1.3147   0.09352   0.08826  -0.0098   0.0128   1.0000
  19.000   1.3126   0.09657   0.09146  -0.0095   0.0126   1.0000
  19.250   1.3092   0.09982   0.09486  -0.0093   0.0123   1.0000
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