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GOE 240 (KOLLER) AIRFOIL (goe240-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 240 (KOLLER) AIRFOIL (goe240-il)
Reynolds number: 200,000
Max Cl/Cd: 78.15 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe240-il-200000-n5.txt
Download as CSV file: xf-goe240-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 240 (KOLLER) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2980   0.09648   0.09313  -0.0274   1.0000   0.0219
  -7.750  -0.3007   0.09447   0.09118  -0.0267   1.0000   0.0227
  -7.500  -0.3094   0.09307   0.08986  -0.0252   1.0000   0.0234
  -7.250  -0.2932   0.08937   0.08618  -0.0329   0.9937   0.0239
  -7.000  -0.2632   0.08426   0.08103  -0.0440   0.9864   0.0241
  -6.750  -0.2360   0.07920   0.07594  -0.0516   0.9795   0.0241
  -6.500  -0.2077   0.07407   0.07076  -0.0588   0.9730   0.0241
  -6.250  -0.1814   0.06916   0.06580  -0.0645   0.9655   0.0241
  -6.000  -0.1509   0.06403   0.06060  -0.0720   0.9554   0.0242
  -5.750  -0.1404   0.06232   0.05894  -0.0693   0.9497   0.0270
  -5.500  -0.0917   0.05746   0.05387  -0.0821   0.9363   0.0318
  -5.250  -0.0637   0.05308   0.04936  -0.0865   0.9226   0.0319
  -5.000  -0.0370   0.04871   0.04486  -0.0900   0.9085   0.0319
  -4.750  -0.0213   0.04578   0.04192  -0.0905   0.8948   0.0340
  -4.250   0.0455   0.03731   0.03298  -0.0986   0.8727   0.0340
  -4.000   0.0753   0.03461   0.03007  -0.1007   0.8636   0.0354
  -3.750   0.1062   0.03171   0.02690  -0.1027   0.8542   0.0373
  -3.500   0.1397   0.02731   0.02203  -0.1049   0.8459   0.0352
  -3.250   0.1699   0.02459   0.01894  -0.1059   0.8381   0.0357
  -3.000   0.1991   0.02258   0.01659  -0.1065   0.8306   0.0374
  -2.750   0.2288   0.02017   0.01372  -0.1069   0.8235   0.0369
  -2.500   0.2577   0.01827   0.01140  -0.1070   0.8161   0.0369
  -2.250   0.2863   0.01688   0.00963  -0.1070   0.8092   0.0372
  -2.000   0.3144   0.01598   0.00846  -0.1069   0.8022   0.0385
  -1.750   0.3422   0.01522   0.00745  -0.1068   0.7944   0.0395
  -1.500   0.3697   0.01448   0.00650  -0.1065   0.7852   0.0394
  -1.250   0.3970   0.01390   0.00574  -0.1061   0.7759   0.0395
  -1.000   0.4240   0.01340   0.00513  -0.1058   0.7651   0.0397
  -0.750   0.4510   0.01299   0.00464  -0.1054   0.7544   0.0401
  -0.500   0.4780   0.01266   0.00422  -0.1051   0.7449   0.0406
  -0.250   0.5051   0.01238   0.00391  -0.1048   0.7354   0.0412
   0.000   0.5323   0.01216   0.00366  -0.1046   0.7264   0.0419
   0.250   0.5595   0.01197   0.00342  -0.1043   0.7171   0.0434
   0.500   0.5866   0.01183   0.00331  -0.1041   0.7065   0.0467
   0.750   0.6138   0.01175   0.00322  -0.1038   0.6960   0.0505
   1.000   0.6408   0.01168   0.00316  -0.1035   0.6843   0.0545
   1.250   0.6676   0.01164   0.00312  -0.1032   0.6698   0.0668
   1.500   0.6942   0.01161   0.00308  -0.1028   0.6517   0.0866
   1.750   0.7203   0.01161   0.00303  -0.1023   0.6288   0.1069
   2.000   0.7451   0.01123   0.00310  -0.1019   0.6007   0.3276
   2.250   0.7694   0.01012   0.00309  -0.1009   0.5738   1.0000
   2.500   0.7947   0.01035   0.00315  -0.1003   0.5526   1.0000
   2.750   0.8202   0.01060   0.00324  -0.0998   0.5331   1.0000
   3.000   0.8454   0.01088   0.00337  -0.0992   0.5131   1.0000
   3.250   0.8702   0.01118   0.00354  -0.0986   0.4912   1.0000
   3.500   0.8951   0.01147   0.00371  -0.0981   0.4665   1.0000
   3.750   0.9198   0.01177   0.00389  -0.0975   0.4390   1.0000
   4.000   0.9440   0.01211   0.00410  -0.0969   0.4082   1.0000
   4.250   0.9677   0.01250   0.00432  -0.0962   0.3771   1.0000
   4.500   0.9911   0.01293   0.00459  -0.0955   0.3497   1.0000
   4.750   1.0147   0.01335   0.00490  -0.0949   0.3281   1.0000
   5.000   1.0387   0.01373   0.00523  -0.0943   0.3101   1.0000
   5.250   1.0627   0.01411   0.00557  -0.0938   0.2934   1.0000
   5.500   1.0866   0.01449   0.00592  -0.0932   0.2767   1.0000
   5.750   1.1103   0.01488   0.00630  -0.0926   0.2593   1.0000
   6.000   1.1336   0.01531   0.00669  -0.0919   0.2411   1.0000
   6.250   1.1563   0.01578   0.00712  -0.0912   0.2212   1.0000
   6.500   1.1768   0.01647   0.00762  -0.0903   0.1898   1.0000
   6.750   1.1965   0.01723   0.00821  -0.0892   0.1639   1.0000
   7.000   1.2177   0.01782   0.00878  -0.0883   0.1491   1.0000
   7.250   1.2387   0.01841   0.00934  -0.0874   0.1350   1.0000
   7.500   1.2596   0.01900   0.00992  -0.0865   0.1210   1.0000
   7.750   1.2791   0.01971   0.01054  -0.0854   0.0954   1.0000
   8.000   1.2923   0.02100   0.01157  -0.0836   0.0564   1.0000
   8.250   1.3099   0.02185   0.01247  -0.0821   0.0457   1.0000
   8.500   1.3244   0.02296   0.01351  -0.0803   0.0228   1.0000
   8.750   1.3388   0.02405   0.01461  -0.0785   0.0177   1.0000
   9.000   1.3534   0.02506   0.01574  -0.0766   0.0160   1.0000
   9.250   1.3661   0.02614   0.01698  -0.0745   0.0147   1.0000
   9.500   1.3750   0.02735   0.01840  -0.0719   0.0138   1.0000
   9.750   1.3831   0.02860   0.01982  -0.0693   0.0131   1.0000
  10.000   1.3915   0.02982   0.02121  -0.0670   0.0124   1.0000
  10.250   1.3977   0.03124   0.02279  -0.0646   0.0117   1.0000
  10.500   1.4017   0.03287   0.02458  -0.0622   0.0113   1.0000
  10.750   1.4039   0.03473   0.02660  -0.0599   0.0109   1.0000
  11.000   1.4045   0.03684   0.02885  -0.0578   0.0106   1.0000
  11.250   1.4040   0.03918   0.03134  -0.0561   0.0103   1.0000
  11.500   1.4026   0.04177   0.03407  -0.0546   0.0101   1.0000
  11.750   1.4002   0.04458   0.03701  -0.0534   0.0099   1.0000
  12.000   1.3968   0.04762   0.04020  -0.0523   0.0097   1.0000
  12.250   1.3926   0.05083   0.04355  -0.0515   0.0095   1.0000
  12.500   1.3875   0.05425   0.04708  -0.0507   0.0094   1.0000
  12.750   1.3812   0.05788   0.05080  -0.0500   0.0092   1.0000
  13.000   1.3743   0.06166   0.05466  -0.0491   0.0089   1.0000
  13.250   1.3740   0.06482   0.05801  -0.0491   0.0087   1.0000
  13.500   1.3724   0.06820   0.06157  -0.0493   0.0085   1.0000
  13.750   1.3699   0.07183   0.06536  -0.0496   0.0083   1.0000
  14.000   1.3665   0.07567   0.06937  -0.0501   0.0081   1.0000
  14.250   1.3623   0.07971   0.07358  -0.0507   0.0079   1.0000
  14.500   1.3573   0.08396   0.07799  -0.0514   0.0078   1.0000
  14.750   1.3519   0.08841   0.08261  -0.0524   0.0077   1.0000
  15.000   1.3458   0.09310   0.08746  -0.0536   0.0076   1.0000
  15.250   1.3388   0.09802   0.09256  -0.0551   0.0076   1.0000
  15.500   1.3311   0.10323   0.09794  -0.0569   0.0075   1.0000
  15.750   1.3227   0.10872   0.10360  -0.0590   0.0074   1.0000
  16.000   1.3137   0.11450   0.10959  -0.0615   0.0074   1.0000
  16.250   1.3042   0.12057   0.11583  -0.0644   0.0074   1.0000
  16.500   1.2941   0.12695   0.12238  -0.0677   0.0073   1.0000
  16.750   1.2836   0.13365   0.12926  -0.0713   0.0073   1.0000
  17.000   1.2728   0.14071   0.13649  -0.0754   0.0073   1.0000
  17.250   1.2615   0.14818   0.14413  -0.0799   0.0074   1.0000
  17.500   1.2499   0.15604   0.15215  -0.0848   0.0074   1.0000
  17.750   1.2378   0.16439   0.16067  -0.0901   0.0074   1.0000
  18.000   1.2253   0.17331   0.16971  -0.0959   0.0075   1.0000
  18.250   1.2121   0.18304   0.17959  -0.1022   0.0076   1.0000
  18.500   1.1979   0.19387   0.19054  -0.1092   0.0077   1.0000
  18.750   1.1824   0.20626   0.20302  -0.1169   0.0079   1.0000
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