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GOE 123 AIRFOIL (goe123-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 123 AIRFOIL (goe123-il)
Reynolds number: 200,000
Max Cl/Cd: 85.02 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe123-il-200000-n5.txt
Download as CSV file: xf-goe123-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 123 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3007   0.10722   0.10375  -0.0298   1.0000   0.0205
  -8.500  -0.3017   0.10556   0.10215  -0.0307   1.0000   0.0205
  -8.250  -0.3084   0.10437   0.10104  -0.0299   0.9987   0.0206
  -8.000  -0.2927   0.09962   0.09629  -0.0330   0.9936   0.0207
  -7.750  -0.2778   0.09499   0.09164  -0.0335   0.9906   0.0211
  -7.500  -0.2609   0.09136   0.08801  -0.0368   0.9847   0.0216
  -7.250  -0.2424   0.08784   0.08448  -0.0410   0.9781   0.0223
  -7.000  -0.2226   0.08433   0.08096  -0.0458   0.9712   0.0233
  -6.750  -0.1972   0.08083   0.07743  -0.0528   0.9642   0.0255
  -6.500  -0.1576   0.07757   0.07408  -0.0669   0.9557   0.0263
  -6.250  -0.1311   0.07377   0.07022  -0.0732   0.9483   0.0264
  -6.000  -0.1034   0.06982   0.06618  -0.0789   0.9425   0.0265
  -5.750  -0.0858   0.06519   0.06153  -0.0815   0.9360   0.0268
  -5.500  -0.0758   0.06200   0.05836  -0.0796   0.9318   0.0277
  -5.250  -0.0569   0.05954   0.05588  -0.0811   0.9248   0.0295
  -5.000  -0.0289   0.05655   0.05281  -0.0853   0.9195   0.0319
  -4.750   0.0218   0.05395   0.04995  -0.0953   0.9125   0.0347
  -4.500   0.0547   0.05098   0.04680  -0.0993   0.9070   0.0349
  -4.250   0.0698   0.04647   0.04230  -0.1003   0.9009   0.0361
  -4.000   0.0895   0.04411   0.03991  -0.1007   0.8932   0.0372
  -3.750   0.1155   0.04179   0.03749  -0.1023   0.8865   0.0388
  -3.500   0.1443   0.03951   0.03507  -0.1044   0.8790   0.0412
  -3.250   0.1941   0.03807   0.03317  -0.1090   0.8743   0.0458
  -3.000   0.2127   0.03442   0.02957  -0.1099   0.8676   0.0473
  -2.750   0.2376   0.03259   0.02767  -0.1106   0.8619   0.0489
  -2.500   0.2660   0.03084   0.02579  -0.1117   0.8565   0.0510
  -2.250   0.3068   0.03027   0.02475  -0.1131   0.8502   0.0571
  -2.000   0.3332   0.02610   0.02047  -0.1143   0.8452   0.0444
  -1.750   0.3630   0.02430   0.01846  -0.1150   0.8387   0.0444
  -1.500   0.3918   0.02258   0.01655  -0.1154   0.8320   0.0433
  -1.250   0.4210   0.02083   0.01457  -0.1157   0.8233   0.0409
  -1.000   0.4514   0.01877   0.01213  -0.1157   0.8139   0.0386
  -0.750   0.4816   0.01666   0.00958  -0.1157   0.8029   0.0373
  -0.500   0.5100   0.01550   0.00816  -0.1155   0.7938   0.0372
  -0.250   0.5380   0.01466   0.00709  -0.1153   0.7855   0.0375
   0.000   0.5655   0.01406   0.00637  -0.1151   0.7764   0.0384
   0.250   0.5929   0.01365   0.00586  -0.1148   0.7681   0.0405
   0.500   0.6202   0.01315   0.00527  -0.1146   0.7580   0.0411
   0.750   0.6474   0.01271   0.00475  -0.1142   0.7481   0.0411
   1.000   0.6745   0.01235   0.00432  -0.1139   0.7378   0.0414
   1.250   0.7016   0.01208   0.00402  -0.1136   0.7262   0.0418
   1.500   0.7285   0.01187   0.00379  -0.1133   0.7138   0.0424
   1.750   0.7554   0.01172   0.00361  -0.1130   0.7001   0.0434
   2.000   0.7823   0.01162   0.00348  -0.1126   0.6854   0.0447
   2.250   0.8090   0.01157   0.00340  -0.1123   0.6690   0.0466
   2.500   0.8353   0.01155   0.00334  -0.1118   0.6487   0.0516
   2.750   0.8610   0.01158   0.00335  -0.1113   0.6209   0.0711
   3.000   0.8858   0.01171   0.00343  -0.1105   0.5873   0.1268
   3.250   0.9103   0.01194   0.00352  -0.1098   0.5535   0.1583
   3.500   0.9347   0.01218   0.00365  -0.1092   0.5243   0.1855
   4.000   0.9794   0.01152   0.00407  -0.1070   0.4730   1.0000
   4.250   1.0037   0.01189   0.00429  -0.1064   0.4483   1.0000
   4.500   1.0284   0.01224   0.00454  -0.1059   0.4252   1.0000
   4.750   1.0527   0.01261   0.00482  -0.1054   0.4042   1.0000
   5.000   1.0769   0.01298   0.00513  -0.1048   0.3845   1.0000
   5.250   1.1011   0.01336   0.00545  -0.1043   0.3667   1.0000
   5.500   1.1249   0.01377   0.00580  -0.1037   0.3485   1.0000
   5.750   1.1483   0.01422   0.00620  -0.1030   0.3296   1.0000
   6.000   1.1716   0.01467   0.00660  -0.1024   0.3128   1.0000
   6.250   1.1953   0.01507   0.00701  -0.1018   0.2993   1.0000
   6.500   1.2185   0.01551   0.00744  -0.1012   0.2835   1.0000
   6.750   1.2408   0.01601   0.00792  -0.1004   0.2618   1.0000
   7.000   1.2622   0.01658   0.00841  -0.0995   0.2354   1.0000
   7.250   1.2826   0.01724   0.00895  -0.0986   0.2015   1.0000
   7.500   1.3014   0.01807   0.00960  -0.0975   0.1661   1.0000
   7.750   1.3165   0.01930   0.01049  -0.0959   0.1064   1.0000
   8.000   1.3298   0.02072   0.01166  -0.0941   0.0704   1.0000
   8.250   1.3432   0.02208   0.01280  -0.0922   0.0383   1.0000
   8.500   1.3587   0.02316   0.01393  -0.0905   0.0311   1.0000
   8.750   1.3723   0.02435   0.01520  -0.0886   0.0265   1.0000
   9.000   1.3874   0.02531   0.01632  -0.0868   0.0240   1.0000
   9.250   1.3995   0.02641   0.01756  -0.0847   0.0218   1.0000
   9.500   1.4066   0.02773   0.01901  -0.0820   0.0200   1.0000
   9.750   1.4112   0.02926   0.02065  -0.0791   0.0186   1.0000
  10.000   1.4202   0.03049   0.02203  -0.0768   0.0175   1.0000
  10.250   1.4261   0.03201   0.02368  -0.0744   0.0166   1.0000
  10.500   1.4310   0.03366   0.02547  -0.0721   0.0158   1.0000
  10.750   1.4351   0.03545   0.02738  -0.0699   0.0152   1.0000
  11.000   1.4387   0.03734   0.02938  -0.0679   0.0146   1.0000
  11.250   1.4408   0.03944   0.03158  -0.0660   0.0139   1.0000
  11.500   1.4392   0.04200   0.03425  -0.0640   0.0133   1.0000
  11.750   1.4395   0.04450   0.03687  -0.0622   0.0128   1.0000
  12.000   1.4434   0.04666   0.03921  -0.0609   0.0123   1.0000
  12.250   1.4452   0.04913   0.04184  -0.0595   0.0119   1.0000
  12.500   1.4461   0.05178   0.04465  -0.0582   0.0115   1.0000
  12.750   1.4465   0.05455   0.04758  -0.0570   0.0112   1.0000
  13.000   1.4463   0.05747   0.05065  -0.0560   0.0109   1.0000
  13.250   1.4452   0.06055   0.05390  -0.0551   0.0107   1.0000
  13.500   1.4429   0.06384   0.05736  -0.0545   0.0105   1.0000
  13.750   1.4394   0.06734   0.06103  -0.0541   0.0103   1.0000
  14.000   1.4348   0.07110   0.06498  -0.0540   0.0101   1.0000
  14.250   1.4291   0.07508   0.06915  -0.0542   0.0099   1.0000
  14.500   1.4226   0.07931   0.07354  -0.0548   0.0098   1.0000
  14.750   1.4154   0.08383   0.07822  -0.0557   0.0096   1.0000
  15.000   1.4075   0.08860   0.08314  -0.0569   0.0095   1.0000
  15.250   1.3983   0.09373   0.08842  -0.0585   0.0093   1.0000
  15.500   1.3873   0.09934   0.09420  -0.0604   0.0092   1.0000
  16.000   1.3613   0.11213   0.10737  -0.0659   0.0090   1.0000
  16.250   1.3482   0.11904   0.11449  -0.0696   0.0090   1.0000
  16.500   1.3347   0.12632   0.12198  -0.0736   0.0090   1.0000
  16.750   1.3209   0.13399   0.12984  -0.0782   0.0089   1.0000
  17.000   1.3071   0.14201   0.13804  -0.0831   0.0089   1.0000
  17.250   1.2931   0.15045   0.14665  -0.0885   0.0089   1.0000
  17.500   1.2791   0.15922   0.15557  -0.0941   0.0090   1.0000
  17.750   1.2651   0.16844   0.16493  -0.1002   0.0090   1.0000
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