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GOE 450 AIRFOIL (goe450-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 450 AIRFOIL (goe450-il)
Reynolds number: 1,000,000
Max Cl/Cd: 118.89 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe450-il-1000000-n5.txt
Download as CSV file: xf-goe450-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 450 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2721   0.08691   0.08513  -0.0596   0.9449   0.0091
  -9.000  -0.2671   0.08373   0.08192  -0.0612   0.9360   0.0095
  -8.750  -0.2654   0.07955   0.07773  -0.0637   0.9269   0.0101
  -8.500  -0.2709   0.07353   0.07168  -0.0680   0.9160   0.0110
  -7.500  -0.2265   0.02027   0.01693  -0.1237   0.8793   0.0174
  -7.250  -0.2005   0.01955   0.01608  -0.1240   0.8741   0.0176
  -7.000  -0.1733   0.01946   0.01596  -0.1241   0.8686   0.0178
  -6.750  -0.1465   0.01925   0.01570  -0.1242   0.8622   0.0180
  -6.500  -0.1199   0.01876   0.01510  -0.1243   0.8563   0.0182
  -6.250  -0.0937   0.01775   0.01393  -0.1246   0.8498   0.0186
  -6.000  -0.0677   0.01661   0.01257  -0.1248   0.8432   0.0190
  -5.750  -0.0412   0.01555   0.01132  -0.1250   0.8358   0.0197
  -5.500  -0.0149   0.01427   0.00976  -0.1251   0.8283   0.0203
  -5.250   0.0120   0.01331   0.00856  -0.1252   0.8201   0.0208
  -5.000   0.0392   0.01270   0.00777  -0.1252   0.8117   0.0212
  -4.750   0.0668   0.01240   0.00735  -0.1252   0.8019   0.0215
  -4.500   0.0940   0.01178   0.00656  -0.1252   0.7920   0.0217
  -4.250   0.1207   0.01093   0.00555  -0.1252   0.7810   0.0221
  -4.000   0.1478   0.01050   0.00501  -0.1251   0.7683   0.0224
  -3.750   0.1750   0.01018   0.00459  -0.1251   0.7541   0.0226
  -3.500   0.2022   0.00989   0.00420  -0.1250   0.7395   0.0228
  -3.250   0.2295   0.00963   0.00385  -0.1249   0.7250   0.0230
  -3.000   0.2568   0.00940   0.00352  -0.1248   0.7104   0.0233
  -2.750   0.2840   0.00919   0.00322  -0.1247   0.6953   0.0235
  -2.500   0.3113   0.00904   0.00298  -0.1246   0.6809   0.0239
  -2.250   0.3388   0.00890   0.00277  -0.1245   0.6682   0.0243
  -2.000   0.3663   0.00872   0.00253  -0.1245   0.6580   0.0247
  -1.750   0.3940   0.00857   0.00232  -0.1244   0.6482   0.0250
  -1.500   0.4218   0.00843   0.00214  -0.1244   0.6397   0.0254
  -1.000   0.4774   0.00825   0.00187  -0.1244   0.6234   0.0262
  -0.500   0.5331   0.00812   0.00168  -0.1244   0.6084   0.0268
  -0.250   0.5607   0.00810   0.00162  -0.1244   0.5997   0.0270
   0.000   0.5884   0.00808   0.00157  -0.1244   0.5883   0.0271
   0.250   0.6157   0.00804   0.00146  -0.1243   0.5741   0.0277
   0.500   0.6429   0.00804   0.00140  -0.1242   0.5583   0.0284
   0.750   0.6703   0.00806   0.00138  -0.1241   0.5450   0.0296
   1.000   0.6977   0.00809   0.00137  -0.1241   0.5337   0.0306
   1.250   0.7250   0.00814   0.00138  -0.1240   0.5212   0.0318
   1.500   0.7517   0.00824   0.00142  -0.1238   0.5020   0.0331
   1.750   0.7776   0.00843   0.00148  -0.1235   0.4746   0.0344
   2.000   0.8036   0.00860   0.00157  -0.1232   0.4502   0.0409
   2.250   0.8300   0.00865   0.00169  -0.1231   0.4324   0.1072
   2.500   0.8560   0.00865   0.00186  -0.1230   0.4105   0.2286
   2.750   0.8817   0.00846   0.00211  -0.1230   0.3896   0.4825
   3.500   0.9559   0.00804   0.00259  -0.1215   0.3412   1.0000
   3.750   0.9815   0.00829   0.00275  -0.1212   0.3224   1.0000
   4.000   1.0063   0.00862   0.00295  -0.1207   0.2971   1.0000
   4.250   1.0307   0.00897   0.00317  -0.1202   0.2706   1.0000
   4.500   1.0476   0.01002   0.00372  -0.1186   0.1791   1.0000
   4.750   1.0708   0.01046   0.00403  -0.1179   0.1544   1.0000
   5.000   1.0954   0.01077   0.00428  -0.1174   0.1401   1.0000
   5.250   1.1177   0.01127   0.00462  -0.1166   0.1086   1.0000
   5.500   1.1396   0.01180   0.00500  -0.1158   0.0808   1.0000
   5.750   1.1635   0.01213   0.00530  -0.1152   0.0716   1.0000
   6.250   1.2073   0.01311   0.00607  -0.1134   0.0356   1.0000
   6.500   1.2307   0.01344   0.00639  -0.1127   0.0317   1.0000
   6.750   1.2544   0.01373   0.00671  -0.1122   0.0307   1.0000
   7.000   1.2776   0.01404   0.00704  -0.1115   0.0294   1.0000
   7.250   1.3001   0.01439   0.00740  -0.1107   0.0280   1.0000
   7.500   1.3220   0.01478   0.00780  -0.1098   0.0264   1.0000
   7.750   1.3433   0.01519   0.00823  -0.1088   0.0247   1.0000
   8.000   1.3647   0.01557   0.00864  -0.1079   0.0237   1.0000
   8.250   1.3864   0.01589   0.00899  -0.1070   0.0230   1.0000
   8.500   1.4073   0.01625   0.00938  -0.1060   0.0220   1.0000
   8.750   1.4269   0.01664   0.00980  -0.1048   0.0205   1.0000
   9.000   1.4442   0.01709   0.01025  -0.1031   0.0188   1.0000
   9.250   1.4612   0.01757   0.01074  -0.1015   0.0175   1.0000
   9.500   1.4786   0.01802   0.01123  -0.0999   0.0164   1.0000
   9.750   1.4950   0.01854   0.01176  -0.0983   0.0149   1.0000
  10.000   1.5102   0.01913   0.01236  -0.0965   0.0134   1.0000
  10.250   1.5258   0.01972   0.01298  -0.0948   0.0125   1.0000
  10.500   1.5403   0.02037   0.01366  -0.0930   0.0114   1.0000
  10.750   1.5538   0.02111   0.01442  -0.0912   0.0104   1.0000
  11.000   1.5671   0.02187   0.01523  -0.0894   0.0098   1.0000
  11.250   1.5803   0.02266   0.01608  -0.0876   0.0093   1.0000
  11.500   1.5925   0.02352   0.01699  -0.0858   0.0087   1.0000
  11.750   1.6039   0.02447   0.01799  -0.0840   0.0082   1.0000
  12.000   1.6141   0.02554   0.01910  -0.0821   0.0078   1.0000
  12.250   1.6229   0.02673   0.02035  -0.0802   0.0073   1.0000
  12.500   1.6331   0.02785   0.02155  -0.0785   0.0071   1.0000
  12.750   1.6424   0.02906   0.02284  -0.0769   0.0068   1.0000
  13.000   1.6510   0.03037   0.02422  -0.0752   0.0065   1.0000
  13.250   1.6586   0.03180   0.02571  -0.0737   0.0062   1.0000
  13.500   1.6652   0.03337   0.02734  -0.0721   0.0060   1.0000
  13.750   1.6705   0.03508   0.02912  -0.0706   0.0057   1.0000
  14.000   1.6744   0.03698   0.03110  -0.0691   0.0055   1.0000
  14.250   1.6761   0.03917   0.03337  -0.0677   0.0053   1.0000
  14.500   1.6800   0.04119   0.03549  -0.0665   0.0052   1.0000
  14.750   1.6831   0.04337   0.03776  -0.0654   0.0051   1.0000
  15.000   1.6854   0.04571   0.04019  -0.0645   0.0050   1.0000
  15.250   1.6870   0.04821   0.04279  -0.0637   0.0049   1.0000
  15.500   1.6876   0.05089   0.04557  -0.0631   0.0048   1.0000
  15.750   1.6874   0.05372   0.04849  -0.0625   0.0047   1.0000
  16.000   1.6865   0.05672   0.05160  -0.0621   0.0045   1.0000
  16.250   1.6847   0.05993   0.05490  -0.0619   0.0044   1.0000
  16.500   1.6822   0.06328   0.05835  -0.0618   0.0044   1.0000
  16.750   1.6782   0.06687   0.06204  -0.0618   0.0043   1.0000
  17.000   1.6736   0.07062   0.06589  -0.0620   0.0042   1.0000
  17.250   1.6682   0.07457   0.06995  -0.0623   0.0041   1.0000
  17.500   1.6615   0.07880   0.07429  -0.0628   0.0040   1.0000
  17.750   1.6537   0.08324   0.07883  -0.0635   0.0040   1.0000
  18.000   1.6446   0.08796   0.08366  -0.0644   0.0039   1.0000
  18.250   1.6347   0.09290   0.08871  -0.0655   0.0038   1.0000
  18.500   1.6234   0.09818   0.09410  -0.0668   0.0038   1.0000
  18.750   1.6109   0.10371   0.09976  -0.0684   0.0037   1.0000
  19.000   1.5976   0.10948   0.10564  -0.0702   0.0037   1.0000
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