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GOE 235 (SCHTTE-LANZ) AIRFOIL (goe235-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 235 (SCHTTE-LANZ) AIRFOIL (goe235-il)
Reynolds number: 50,000
Max Cl/Cd: 37.54 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe235-il-50000-n5.txt
Download as CSV file: xf-goe235-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 235 (SCHTTE-LANZ) AIRFOIL                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4381   0.11111   0.10374  -0.0020   1.0000   0.0964
  -8.250  -0.4430   0.11023   0.10296  -0.0068   1.0000   0.0986
  -8.000  -0.4434   0.10904   0.10186  -0.0148   1.0000   0.0994
  -7.750  -0.4237   0.10197   0.09478  -0.0073   1.0000   0.1023
  -7.500  -0.4137   0.09859   0.09144  -0.0075   1.0000   0.1053
  -7.250  -0.4057   0.09565   0.08854  -0.0095   1.0000   0.1090
  -7.000  -0.3994   0.09373   0.08665  -0.0174   1.0000   0.1139
  -6.750  -0.3891   0.09040   0.08336  -0.0224   1.0000   0.1156
  -6.500  -0.3776   0.08609   0.07912  -0.0187   1.0000   0.1185
  -6.250  -0.3656   0.08297   0.07604  -0.0193   1.0000   0.1231
  -6.000  -0.3491   0.08124   0.07420  -0.0306   1.0000   0.1313
  -5.750  -0.3406   0.07676   0.06986  -0.0255   1.0000   0.1348
  -5.250  -0.3142   0.07093   0.06409  -0.0291   1.0000   0.1511
  -4.750  -0.2887   0.06545   0.05868  -0.0307   1.0000   0.1690
  -4.250  -0.2620   0.06098   0.05419  -0.0327   1.0000   0.1957
  -4.000  -0.2532   0.05815   0.05146  -0.0313   1.0000   0.2043
  -3.750  -0.2421   0.05595   0.04928  -0.0310   1.0000   0.2208
  -3.500  -0.2317   0.05383   0.04721  -0.0303   1.0000   0.2391
  -3.000  -0.2123   0.05005   0.04350  -0.0283   1.0000   0.3014
  -2.500  -0.0865   0.04162   0.03344  -0.0478   0.9928   0.1119
  -2.250  -0.0424   0.03855   0.02998  -0.0518   0.9855   0.0950
  -2.000   0.0048   0.03638   0.02706  -0.0556   0.9776   0.0844
  -1.750   0.0432   0.03407   0.02465  -0.0587   0.9706   0.0822
  -1.500   0.0823   0.03230   0.02263  -0.0614   0.9625   0.0809
  -1.250   0.1216   0.03087   0.02089  -0.0640   0.9544   0.0816
  -1.000   0.1635   0.02951   0.01924  -0.0668   0.9466   0.0819
  -0.750   0.2031   0.02825   0.01775  -0.0690   0.9360   0.0811
  -0.500   0.2453   0.02706   0.01635  -0.0714   0.9248   0.0807
  -0.250   0.2867   0.02599   0.01508  -0.0733   0.9112   0.0807
   0.000   0.3250   0.02510   0.01401  -0.0743   0.8951   0.0827
   0.250   0.3613   0.02427   0.01303  -0.0747   0.8780   0.0857
   0.500   0.3953   0.02341   0.01212  -0.0746   0.8596   0.0880
   0.750   0.4266   0.02273   0.01139  -0.0740   0.8408   0.0900
   1.000   0.4557   0.02219   0.01079  -0.0730   0.8222   0.0926
   1.250   0.4833   0.02178   0.01029  -0.0717   0.8028   0.0980
   1.500   0.5081   0.02140   0.00994  -0.0703   0.7798   0.1045
   1.750   0.5335   0.02109   0.00960  -0.0688   0.7568   0.1112
   2.000   0.5589   0.02081   0.00938  -0.0676   0.7343   0.1224
   2.250   0.5847   0.02046   0.00927  -0.0666   0.7118   0.1554
   2.500   0.6074   0.01856   0.00909  -0.0646   0.6899   1.0000
   2.750   0.6325   0.01866   0.00896  -0.0630   0.6635   1.0000
   3.000   0.6574   0.01878   0.00884  -0.0614   0.6347   1.0000
   3.250   0.6817   0.01897   0.00882  -0.0599   0.6010   1.0000
   3.500   0.7054   0.01923   0.00893  -0.0584   0.5592   1.0000
   3.750   0.7287   0.01955   0.00910  -0.0570   0.5038   1.0000
   4.000   0.7511   0.02001   0.00916  -0.0554   0.4521   1.0000
   4.250   0.7738   0.02070   0.00946  -0.0542   0.4116   1.0000
   4.500   0.7969   0.02148   0.00995  -0.0533   0.3784   1.0000
   4.750   0.8201   0.02223   0.01050  -0.0525   0.3487   1.0000
   5.000   0.8436   0.02293   0.01108  -0.0519   0.3236   1.0000
   5.250   0.8672   0.02360   0.01167  -0.0513   0.3045   1.0000
   5.500   0.8909   0.02427   0.01229  -0.0506   0.2887   1.0000
   5.750   0.9146   0.02493   0.01296  -0.0500   0.2757   1.0000
   6.000   0.9370   0.02564   0.01366  -0.0493   0.2572   1.0000
   6.250   0.9579   0.02644   0.01436  -0.0485   0.2353   1.0000
   6.500   0.9795   0.02719   0.01514  -0.0478   0.2135   1.0000
   6.750   1.0013   0.02792   0.01601  -0.0471   0.1917   1.0000
   7.000   1.0227   0.02868   0.01687  -0.0463   0.1636   1.0000
   7.250   1.0449   0.02947   0.01778  -0.0455   0.1197   1.0000
   7.500   1.0625   0.03079   0.01872  -0.0446   0.0966   1.0000
   7.750   1.0794   0.03231   0.02006  -0.0435   0.0880   1.0000
   8.000   1.0957   0.03390   0.02163  -0.0424   0.0823   1.0000
   8.250   1.1108   0.03559   0.02330  -0.0411   0.0784   1.0000
   8.500   1.1274   0.03709   0.02497  -0.0399   0.0756   1.0000
   8.750   1.1433   0.03867   0.02672  -0.0386   0.0736   1.0000
   9.000   1.1588   0.04033   0.02851  -0.0373   0.0718   1.0000
   9.250   1.1741   0.04208   0.03037  -0.0360   0.0703   1.0000
   9.500   1.1893   0.04399   0.03232  -0.0347   0.0688   1.0000
   9.750   1.2053   0.04597   0.03442  -0.0335   0.0673   1.0000
  10.000   1.2199   0.04796   0.03673  -0.0323   0.0656   1.0000
  10.250   1.2328   0.05013   0.03917  -0.0311   0.0640   1.0000
  10.500   1.2448   0.05249   0.04177  -0.0299   0.0629   1.0000
  10.750   1.2550   0.05505   0.04459  -0.0287   0.0621   1.0000
  11.000   1.2620   0.05781   0.04761  -0.0274   0.0615   1.0000
  11.250   1.2643   0.06074   0.05080  -0.0259   0.0610   1.0000
  11.500   1.2629   0.06390   0.05424  -0.0245   0.0605   1.0000
  11.750   1.2584   0.06733   0.05791  -0.0236   0.0599   1.0000
  12.000   1.2512   0.07110   0.06190  -0.0231   0.0594   1.0000
  12.250   1.2412   0.07531   0.06632  -0.0232   0.0590   1.0000
  12.500   1.2271   0.08017   0.07142  -0.0242   0.0587   1.0000
  12.750   1.2039   0.08648   0.07801  -0.0267   0.0588   1.0000
  13.000   1.1491   0.09912   0.09109  -0.0355   0.0603   1.0000
  13.250   1.0567   0.12621   0.11856  -0.0552   0.0638   1.0000
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