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GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL (goe188-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL (goe188-il)
Reynolds number: 100,000
Max Cl/Cd: 57.13 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe188-il-100000-n5.txt
Download as CSV file: xf-goe188-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3355   0.10474   0.10011  -0.0261   1.0000   0.0247
  -8.000  -0.3331   0.10208   0.09752  -0.0281   1.0000   0.0248
  -7.750  -0.3311   0.09939   0.09492  -0.0301   1.0000   0.0249
  -7.500  -0.3258   0.09638   0.09196  -0.0331   1.0000   0.0250
  -7.250  -0.3196   0.09332   0.08895  -0.0359   1.0000   0.0250
  -7.000  -0.3134   0.09030   0.08598  -0.0382   1.0000   0.0251
  -6.750  -0.3078   0.08741   0.08312  -0.0399   1.0000   0.0251
  -6.500  -0.3039   0.08475   0.08049  -0.0407   1.0000   0.0252
  -6.250  -0.3060   0.07936   0.07528  -0.0374   0.9980   0.0260
  -6.000  -0.2872   0.07480   0.07073  -0.0394   0.9891   0.0276
  -5.750  -0.2599   0.07031   0.06618  -0.0453   0.9778   0.0296
  -5.500  -0.2295   0.06585   0.06162  -0.0520   0.9644   0.0321
  -5.250  -0.1830   0.06217   0.05758  -0.0623   0.9495   0.0356
  -5.000  -0.1538   0.05714   0.05237  -0.0671   0.9388   0.0367
  -4.750  -0.1340   0.05285   0.04813  -0.0687   0.9282   0.0391
  -4.500  -0.1033   0.04938   0.04448  -0.0722   0.9170   0.0430
  -4.250  -0.0627   0.04645   0.04100  -0.0768   0.9062   0.0485
  -4.000  -0.0397   0.04239   0.03699  -0.0785   0.8969   0.0522
  -3.750  -0.0049   0.04018   0.03424  -0.0809   0.8861   0.0625
  -3.500   0.0187   0.03691   0.03097  -0.0819   0.8756   0.0686
  -3.250   0.0469   0.03444   0.02822  -0.0830   0.8647   0.0820
  -3.000   0.0733   0.03230   0.02578  -0.0839   0.8519   0.1077
  -2.500   0.1443   0.02823   0.02055  -0.0820   0.8258   0.0459
  -2.250   0.1746   0.02612   0.01800  -0.0813   0.8138   0.0344
  -2.000   0.2028   0.02430   0.01589  -0.0810   0.8024   0.0328
  -1.750   0.2319   0.02276   0.01401  -0.0805   0.7921   0.0301
  -1.500   0.2617   0.02154   0.01237  -0.0797   0.7828   0.0270
  -1.250   0.2906   0.02079   0.01131  -0.0790   0.7725   0.0257
  -1.000   0.3185   0.01995   0.01028  -0.0785   0.7626   0.0252
  -0.750   0.3459   0.01878   0.00899  -0.0779   0.7535   0.0256
  -0.500   0.3720   0.01768   0.00790  -0.0774   0.7434   0.0286
  -0.250   0.3983   0.01703   0.00717  -0.0768   0.7333   0.0302
   0.000   0.4252   0.01654   0.00652  -0.0763   0.7238   0.0317
   0.250   0.4524   0.01623   0.00600  -0.0758   0.7134   0.0355
   0.500   0.4796   0.01593   0.00553  -0.0755   0.7025   0.0433
   0.750   0.5074   0.01560   0.00521  -0.0752   0.6918   0.0887
   1.250   0.5609   0.01354   0.00488  -0.0741   0.6699   1.0000
   1.500   0.5875   0.01367   0.00482  -0.0738   0.6576   1.0000
   1.750   0.6140   0.01380   0.00479  -0.0735   0.6449   1.0000
   2.000   0.6404   0.01394   0.00479  -0.0731   0.6318   1.0000
   2.250   0.6668   0.01410   0.00482  -0.0728   0.6184   1.0000
   2.500   0.6931   0.01426   0.00488  -0.0725   0.6044   1.0000
   2.750   0.7193   0.01443   0.00497  -0.0722   0.5895   1.0000
   3.000   0.7453   0.01461   0.00507  -0.0718   0.5739   1.0000
   3.250   0.7713   0.01481   0.00520  -0.0715   0.5580   1.0000
   3.500   0.7972   0.01502   0.00536  -0.0712   0.5419   1.0000
   3.750   0.8229   0.01524   0.00553  -0.0708   0.5257   1.0000
   4.000   0.8485   0.01549   0.00571  -0.0705   0.5100   1.0000
   4.250   0.8740   0.01576   0.00596  -0.0701   0.4948   1.0000
   4.500   0.8992   0.01606   0.00620  -0.0697   0.4788   1.0000
   4.750   0.9241   0.01638   0.00647  -0.0693   0.4624   1.0000
   5.000   0.9489   0.01674   0.00681  -0.0689   0.4477   1.0000
   5.250   0.9738   0.01712   0.00717  -0.0685   0.4353   1.0000
   5.500   0.9988   0.01751   0.00760  -0.0682   0.4245   1.0000
   5.750   1.0238   0.01792   0.00810  -0.0679   0.4142   1.0000
   6.000   1.0487   0.01836   0.00858  -0.0675   0.4047   1.0000
   6.250   1.0734   0.01880   0.00909  -0.0672   0.3951   1.0000
   6.500   1.0982   0.01925   0.00967  -0.0669   0.3861   1.0000
   6.750   1.1228   0.01974   0.01026  -0.0665   0.3782   1.0000
   7.000   1.1471   0.02021   0.01092  -0.0661   0.3687   1.0000
   7.250   1.1705   0.02068   0.01154  -0.0656   0.3570   1.0000
   7.500   1.1927   0.02114   0.01213  -0.0649   0.3424   1.0000
   7.750   1.2142   0.02160   0.01278  -0.0641   0.3266   1.0000
   8.000   1.2356   0.02210   0.01344  -0.0632   0.3119   1.0000
   8.250   1.2565   0.02261   0.01414  -0.0624   0.2969   1.0000
   8.500   1.2770   0.02314   0.01488  -0.0614   0.2813   1.0000
   8.750   1.2933   0.02373   0.01556  -0.0600   0.2507   1.0000
   9.000   1.3039   0.02478   0.01637  -0.0580   0.1960   1.0000
   9.250   1.3096   0.02649   0.01772  -0.0556   0.1408   1.0000
   9.500   1.3099   0.02875   0.01962  -0.0528   0.0823   1.0000
   9.750   1.3081   0.03108   0.02176  -0.0497   0.0505   1.0000
  10.250   1.3005   0.03548   0.02610  -0.0432   0.0196   1.0000
  10.500   1.2979   0.03784   0.02860  -0.0409   0.0172   1.0000
  10.750   1.2952   0.04039   0.03137  -0.0391   0.0157   1.0000
  11.000   1.2911   0.04326   0.03447  -0.0378   0.0144   1.0000
  11.250   1.2852   0.04653   0.03793  -0.0370   0.0134   1.0000
  11.500   1.2774   0.05021   0.04180  -0.0366   0.0125   1.0000
  11.750   1.2680   0.05427   0.04607  -0.0365   0.0119   1.0000
  12.000   1.2576   0.05866   0.05066  -0.0368   0.0115   1.0000
  12.250   1.2466   0.06328   0.05548  -0.0374   0.0112   1.0000
  12.500   1.2358   0.06800   0.06040  -0.0381   0.0110   1.0000
  12.750   1.2255   0.07270   0.06529  -0.0387   0.0108   1.0000
  13.000   1.2181   0.07708   0.06981  -0.0393   0.0106   1.0000
  13.250   1.2124   0.08128   0.07419  -0.0399   0.0105   1.0000
  13.500   1.2078   0.08537   0.07845  -0.0404   0.0103   1.0000
  13.750   1.2042   0.08937   0.08263  -0.0408   0.0102   1.0000
  14.000   1.2009   0.09343   0.08687  -0.0412   0.0100   1.0000
  14.250   1.1973   0.09772   0.09135  -0.0420   0.0098   1.0000
  14.500   1.1928   0.10229   0.09611  -0.0432   0.0095   1.0000
  14.750   1.1871   0.10726   0.10127  -0.0448   0.0093   1.0000
  15.000   1.1806   0.11256   0.10676  -0.0468   0.0091   1.0000
  15.250   1.1734   0.11817   0.11256  -0.0491   0.0089   1.0000
  15.500   1.1652   0.12415   0.11872  -0.0519   0.0088   1.0000
  15.750   1.1563   0.13050   0.12527  -0.0551   0.0088   1.0000
  16.000   1.1469   0.13725   0.13219  -0.0587   0.0087   1.0000
  16.250   1.1366   0.14455   0.13967  -0.0628   0.0087   1.0000
  16.500   1.1256   0.15240   0.14768  -0.0674   0.0088   1.0000
  16.750   1.1138   0.16092   0.15635  -0.0725   0.0090   1.0000
  17.000   1.1017   0.17006   0.16563  -0.0779   0.0094   1.0000
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