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GOE 550 AIRFOIL (goe550-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 550 AIRFOIL (goe550-il)
Reynolds number: 200,000
Max Cl/Cd: 76.26 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe550-il-200000.txt
Download as CSV file: xf-goe550-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 550 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.6140   0.06364   0.05985  -0.0702   1.0000   0.0629
 -11.000  -0.7509   0.04607   0.04205  -0.0814   1.0000   0.0592
 -10.750  -0.7803   0.04160   0.03730  -0.0810   1.0000   0.0594
 -10.500  -0.7941   0.03833   0.03371  -0.0797   1.0000   0.0601
 -10.250  -0.7991   0.03573   0.03074  -0.0783   1.0000   0.0613
 -10.000  -0.7980   0.03320   0.02791  -0.0769   1.0000   0.0626
  -9.750  -0.7717   0.03200   0.02678  -0.0782   0.9975   0.0646
  -9.500  -0.7355   0.03081   0.02543  -0.0814   0.9935   0.0675
  -9.250  -0.7038   0.02897   0.02319  -0.0842   0.9880   0.0703
  -9.000  -0.6700   0.02703   0.02103  -0.0871   0.9838   0.0731
  -8.750  -0.6361   0.02632   0.02033  -0.0890   0.9787   0.0761
  -8.500  -0.6011   0.02523   0.01898  -0.0913   0.9735   0.0797
  -8.250  -0.5634   0.02380   0.01730  -0.0942   0.9702   0.0833
  -8.000  -0.5335   0.02312   0.01666  -0.0950   0.9630   0.0869
  -7.750  -0.4958   0.02231   0.01561  -0.0974   0.9588   0.0916
  -7.500  -0.4597   0.02121   0.01445  -0.0995   0.9549   0.0965
  -7.250  -0.4294   0.02063   0.01383  -0.1003   0.9476   0.1018
  -7.000  -0.3918   0.01968   0.01275  -0.1025   0.9440   0.1086
  -6.750  -0.3506   0.01908   0.01209  -0.1052   0.9416   0.1169
  -6.500  -0.3258   0.01844   0.01147  -0.1049   0.9328   0.1243
  -6.250  -0.2867   0.01785   0.01079  -0.1071   0.9293   0.1347
  -6.000  -0.2446   0.01747   0.01037  -0.1099   0.9271   0.1459
  -5.750  -0.2169   0.01722   0.01019  -0.1098   0.9190   0.1542
  -5.500  -0.1775   0.01689   0.00980  -0.1120   0.9153   0.1644
  -5.250  -0.1356   0.01671   0.00952  -0.1145   0.9125   0.1750
  -5.000  -0.1026   0.01652   0.00940  -0.1154   0.9064   0.1827
  -4.750  -0.0685   0.01629   0.00904  -0.1164   0.9002   0.1923
  -4.500  -0.0293   0.01611   0.00891  -0.1183   0.8964   0.2012
  -4.250   0.0011   0.01592   0.00866  -0.1186   0.8888   0.2101
  -4.000   0.0353   0.01586   0.00856  -0.1195   0.8824   0.2201
  -3.750   0.0723   0.01562   0.00832  -0.1211   0.8775   0.2293
  -3.500   0.0985   0.01560   0.00817  -0.1205   0.8677   0.2387
  -3.250   0.1341   0.01528   0.00789  -0.1217   0.8621   0.2466
  -3.000   0.1596   0.01523   0.00772  -0.1210   0.8519   0.2548
  -2.750   0.1932   0.01493   0.00742  -0.1218   0.8455   0.2621
  -2.500   0.2184   0.01489   0.00732  -0.1211   0.8351   0.2698
  -2.250   0.2506   0.01465   0.00700  -0.1216   0.8279   0.2769
  -2.000   0.2757   0.01453   0.00689  -0.1208   0.8169   0.2830
  -1.750   0.3041   0.01445   0.00666  -0.1206   0.8067   0.2895
  -1.500   0.3326   0.01415   0.00636  -0.1204   0.7962   0.2952
  -1.250   0.3582   0.01406   0.00625  -0.1196   0.7848   0.3015
  -1.000   0.3873   0.01395   0.00602  -0.1195   0.7762   0.3081
  -0.750   0.4128   0.01379   0.00592  -0.1189   0.7656   0.3140
  -0.500   0.4401   0.01375   0.00582  -0.1185   0.7562   0.3217
  -0.250   0.4671   0.01358   0.00568  -0.1181   0.7466   0.3291
   0.000   0.4931   0.01352   0.00562  -0.1175   0.7366   0.3364
   0.250   0.5214   0.01340   0.00545  -0.1173   0.7279   0.3429
   0.500   0.5463   0.01330   0.00542  -0.1165   0.7171   0.3500
   1.000   0.5994   0.01313   0.00528  -0.1155   0.6978   0.3655
   1.250   0.6257   0.01310   0.00526  -0.1150   0.6882   0.3753
   1.500   0.6523   0.01300   0.00522  -0.1145   0.6786   0.3873
   1.750   0.6771   0.01295   0.00528  -0.1137   0.6678   0.4024
   2.000   0.7037   0.01290   0.00528  -0.1133   0.6586   0.4244
   2.250   0.7281   0.01281   0.00536  -0.1124   0.6479   0.4594
   2.500   0.7516   0.01257   0.00543  -0.1114   0.6379   0.5369
   2.750   0.7963   0.01169   0.00545  -0.1142   0.6273   1.0000
   3.000   0.8200   0.01183   0.00554  -0.1132   0.6154   1.0000
   3.250   0.8450   0.01199   0.00562  -0.1124   0.6045   1.0000
   3.500   0.8712   0.01217   0.00568  -0.1118   0.5943   1.0000
   3.750   0.8946   0.01234   0.00584  -0.1108   0.5821   1.0000
   4.000   0.9187   0.01253   0.00597  -0.1099   0.5697   1.0000
   4.250   0.9430   0.01274   0.00609  -0.1090   0.5573   1.0000
   4.500   0.9673   0.01295   0.00621  -0.1080   0.5445   1.0000
   4.750   0.9899   0.01316   0.00641  -0.1069   0.5310   1.0000
   5.000   1.0131   0.01341   0.00663  -0.1058   0.5184   1.0000
   5.250   1.0370   0.01369   0.00687  -0.1049   0.5069   1.0000
   5.500   1.0609   0.01398   0.00707  -0.1040   0.4952   1.0000
   5.750   1.0826   0.01422   0.00733  -0.1027   0.4821   1.0000
   6.000   1.1050   0.01449   0.00761  -0.1016   0.4701   1.0000
   6.250   1.1284   0.01481   0.00788  -0.1007   0.4599   1.0000
   6.500   1.1507   0.01510   0.00818  -0.0996   0.4492   1.0000
   6.750   1.1729   0.01541   0.00851  -0.0984   0.4388   1.0000
   7.000   1.1957   0.01576   0.00880  -0.0974   0.4291   1.0000
   7.250   1.2158   0.01603   0.00913  -0.0959   0.4177   1.0000
   7.500   1.2352   0.01632   0.00943  -0.0943   0.4052   1.0000
   7.750   1.2538   0.01663   0.00973  -0.0925   0.3925   1.0000
   8.000   1.2719   0.01698   0.01004  -0.0908   0.3800   1.0000
   8.250   1.2896   0.01732   0.01042  -0.0889   0.3681   1.0000
   8.500   1.3068   0.01768   0.01082  -0.0870   0.3563   1.0000
   8.750   1.3227   0.01808   0.01124  -0.0849   0.3441   1.0000
   9.000   1.3365   0.01852   0.01166  -0.0824   0.3313   1.0000
   9.250   1.3471   0.01895   0.01210  -0.0794   0.3176   1.0000
   9.500   1.3566   0.01942   0.01260  -0.0762   0.3026   1.0000
   9.750   1.3648   0.01997   0.01316  -0.0730   0.2860   1.0000
  10.000   1.3723   0.02059   0.01381  -0.0698   0.2660   1.0000
  10.250   1.3765   0.02140   0.01459  -0.0664   0.2405   1.0000
  10.500   1.3764   0.02255   0.01560  -0.0627   0.2081   1.0000
  10.750   1.3722   0.02410   0.01696  -0.0589   0.1744   1.0000
  11.000   1.3666   0.02595   0.01862  -0.0554   0.1511   1.0000
  11.250   1.3629   0.02786   0.02044  -0.0524   0.1346   1.0000
  11.500   1.3586   0.02994   0.02247  -0.0496   0.1216   1.0000
  11.750   1.3531   0.03227   0.02476  -0.0472   0.1103   1.0000
  12.000   1.3514   0.03446   0.02696  -0.0452   0.0987   1.0000
  12.250   1.3504   0.03671   0.02924  -0.0435   0.0881   1.0000
  12.500   1.3485   0.03912   0.03167  -0.0420   0.0796   1.0000
  12.750   1.3434   0.04195   0.03444  -0.0407   0.0735   1.0000
  13.000   1.3444   0.04432   0.03689  -0.0397   0.0673   1.0000
  13.250   1.3377   0.04751   0.04004  -0.0387   0.0635   1.0000
  13.500   1.3386   0.05008   0.04272  -0.0380   0.0594   1.0000
  13.750   1.3362   0.05305   0.04573  -0.0375   0.0563   1.0000
  14.000   1.3325   0.05621   0.04889  -0.0369   0.0537   1.0000
  14.250   1.3343   0.05891   0.05170  -0.0366   0.0509   1.0000
  14.500   1.3346   0.06180   0.05463  -0.0363   0.0487   1.0000
  14.750   1.3346   0.06463   0.05739  -0.0358   0.0466   1.0000
  15.000   1.3380   0.06727   0.06017  -0.0355   0.0449   1.0000
  15.250   1.3417   0.06991   0.06291  -0.0353   0.0432   1.0000
  15.500   1.3456   0.07252   0.06556  -0.0352   0.0416   1.0000
  15.750   1.3517   0.07477   0.06778  -0.0349   0.0402   1.0000
  16.000   1.3589   0.07698   0.07004  -0.0343   0.0387   1.0000
  16.250   1.3618   0.07991   0.07313  -0.0345   0.0376   1.0000
  16.500   1.3651   0.08279   0.07614  -0.0348   0.0365   1.0000
  16.750   1.3696   0.08550   0.07893  -0.0349   0.0355   1.0000
  17.000   1.3765   0.08786   0.08132  -0.0349   0.0346   1.0000
  17.250   1.3947   0.08877   0.08214  -0.0335   0.0333   1.0000
  17.500   1.3901   0.09289   0.08650  -0.0346   0.0329   1.0000
  17.750   1.3854   0.09713   0.09096  -0.0358   0.0325   1.0000
  18.000   1.3800   0.10156   0.09561  -0.0373   0.0319   1.0000
  18.250   1.3739   0.10617   0.10042  -0.0390   0.0314   1.0000
  18.500   1.3682   0.11080   0.10523  -0.0409   0.0309   1.0000
  18.750   1.3625   0.11543   0.11001  -0.0429   0.0304   1.0000
  19.000   1.3572   0.12007   0.11480  -0.0450   0.0300   1.0000
  19.250   1.3494   0.12522   0.12012  -0.0476   0.0296   1.0000
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