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GOE 374 AIRFOIL (goe374-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 374 AIRFOIL (goe374-il)
Reynolds number: 100,000
Max Cl/Cd: 57.08 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe374-il-100000-n5.txt
Download as CSV file: xf-goe374-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 374 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
  ------ -------- --------- --------- -------- -------- --------
  -7.000  -0.3113   0.09029   0.08588  -0.0220   1.0000   0.0227
  -6.750  -0.3076   0.08730   0.08293  -0.0218   1.0000   0.0231
  -6.500  -0.3039   0.08461   0.08031  -0.0221   1.0000   0.0234
  -6.250  -0.3005   0.08195   0.07771  -0.0223   1.0000   0.0239
  -6.000  -0.2969   0.07938   0.07519  -0.0226   1.0000   0.0247
  -5.750  -0.2927   0.07689   0.07274  -0.0231   1.0000   0.0252
  -5.500  -0.2878   0.07436   0.07026  -0.0236   1.0000   0.0258
  -5.250  -0.2815   0.07184   0.06776  -0.0243   1.0000   0.0267
  -5.000  -0.2737   0.06928   0.06520  -0.0250   1.0000   0.0272
  -4.750  -0.2300   0.06478   0.06056  -0.0342   0.9925   0.0289
  -4.500  -0.1767   0.06067   0.05617  -0.0445   0.9835   0.0297
  -4.250  -0.1292   0.05672   0.05192  -0.0518   0.9744   0.0299
  -4.000  -0.0886   0.05229   0.04730  -0.0571   0.9664   0.0302
  -3.750  -0.0673   0.04724   0.04232  -0.0593   0.9570   0.0313
  -3.500  -0.0346   0.04372   0.03867  -0.0626   0.9485   0.0336
  -3.250   0.0159   0.04124   0.03565  -0.0674   0.9408   0.0393
  -3.000   0.0395   0.03740   0.03187  -0.0692   0.9306   0.0431
  -2.750   0.0792   0.03499   0.02901  -0.0717   0.9209   0.0515
  -2.500   0.1147   0.03282   0.02651  -0.0738   0.9114   0.0652
  -2.250   0.1418   0.03003   0.02364  -0.0750   0.8987   0.0810
  -1.750   0.2138   0.02549   0.01813  -0.0750   0.8736   0.0484
  -1.500   0.2454   0.02313   0.01544  -0.0752   0.8596   0.0445
  -1.250   0.2776   0.02181   0.01369  -0.0751   0.8443   0.0478
  -1.000   0.3086   0.02025   0.01178  -0.0749   0.8281   0.0466
  -0.750   0.3385   0.01930   0.01046  -0.0745   0.8099   0.0488
  -0.500   0.3670   0.01830   0.00918  -0.0739   0.7897   0.0508
  -0.250   0.3955   0.01740   0.00808  -0.0734   0.7687   0.0509
   0.000   0.4224   0.01661   0.00715  -0.0727   0.7453   0.0514
   0.250   0.4488   0.01597   0.00643  -0.0720   0.7212   0.0544
   0.500   0.4751   0.01558   0.00591  -0.0713   0.6970   0.0588
   0.750   0.5011   0.01526   0.00541  -0.0705   0.6733   0.0587
   1.000   0.5273   0.01510   0.00501  -0.0697   0.6513   0.0588
   1.250   0.5537   0.01505   0.00474  -0.0692   0.6297   0.0591
   1.500   0.5800   0.01508   0.00454  -0.0686   0.6096   0.0597
   1.750   0.6061   0.01515   0.00443  -0.0681   0.5899   0.0608
   2.000   0.6320   0.01525   0.00437  -0.0675   0.5708   0.0625
   2.250   0.6579   0.01536   0.00437  -0.0670   0.5525   0.0664
   2.500   0.6837   0.01546   0.00442  -0.0665   0.5355   0.0840
   3.000   0.7474   0.01418   0.00468  -0.0684   0.5016   1.0000
   3.250   0.7723   0.01446   0.00482  -0.0678   0.4873   1.0000
   3.500   0.7970   0.01475   0.00501  -0.0672   0.4731   1.0000
   3.750   0.8214   0.01506   0.00521  -0.0665   0.4585   1.0000
   4.000   0.8457   0.01539   0.00544  -0.0658   0.4433   1.0000
   4.250   0.8697   0.01572   0.00573  -0.0651   0.4275   1.0000
   4.500   0.8935   0.01606   0.00601  -0.0644   0.4118   1.0000
   4.750   0.9175   0.01641   0.00633  -0.0638   0.3979   1.0000
   5.000   0.9416   0.01677   0.00669  -0.0631   0.3858   1.0000
   5.250   0.9655   0.01713   0.00710  -0.0625   0.3739   1.0000
   5.500   0.9894   0.01748   0.00750  -0.0618   0.3611   1.0000
   5.750   1.0131   0.01783   0.00793  -0.0612   0.3479   1.0000
   6.000   1.0366   0.01819   0.00842  -0.0605   0.3348   1.0000
   6.250   1.0599   0.01857   0.00890  -0.0597   0.3217   1.0000
   6.500   1.0829   0.01898   0.00941  -0.0590   0.3083   1.0000
   6.750   1.1056   0.01941   0.00995  -0.0582   0.2944   1.0000
   7.000   1.1268   0.01986   0.01045  -0.0572   0.2750   1.0000
   7.250   1.1459   0.02040   0.01097  -0.0560   0.2432   1.0000
   7.500   1.1650   0.02107   0.01158  -0.0549   0.2129   1.0000
   7.750   1.1836   0.02184   0.01229  -0.0538   0.1822   1.0000
   8.000   1.1991   0.02295   0.01314  -0.0524   0.1404   1.0000
   8.250   1.2143   0.02418   0.01419  -0.0509   0.1081   1.0000
   8.750   1.2297   0.02818   0.01766  -0.0463   0.0226   1.0000
   9.000   1.2404   0.02974   0.01941  -0.0442   0.0197   1.0000
   9.250   1.2497   0.03135   0.02126  -0.0419   0.0175   1.0000
   9.500   1.2582   0.03288   0.02308  -0.0397   0.0164   1.0000
   9.750   1.2629   0.03452   0.02499  -0.0370   0.0159   1.0000
  10.000   1.2634   0.03633   0.02703  -0.0341   0.0154   1.0000
  10.250   1.2619   0.03832   0.02927  -0.0314   0.0150   1.0000
  10.500   1.2579   0.04065   0.03182  -0.0291   0.0147   1.0000
  10.750   1.2522   0.04332   0.03470  -0.0274   0.0144   1.0000
  11.000   1.2464   0.04625   0.03783  -0.0264   0.0141   1.0000
  11.250   1.2390   0.04966   0.04144  -0.0260   0.0137   1.0000
  11.500   1.2306   0.05352   0.04548  -0.0262   0.0133   1.0000
  11.750   1.2226   0.05763   0.04977  -0.0270   0.0129   1.0000
  12.000   1.2151   0.06192   0.05422  -0.0280   0.0127   1.0000
  12.250   1.2088   0.06619   0.05864  -0.0291   0.0126   1.0000
  12.500   1.2007   0.07081   0.06340  -0.0304   0.0121   1.0000
  12.750   1.1941   0.07529   0.06807  -0.0316   0.0118   1.0000
  13.000   1.1896   0.07946   0.07236  -0.0324   0.0116   1.0000
  13.250   1.1871   0.08340   0.07645  -0.0331   0.0115   1.0000
  13.500   1.1846   0.08739   0.08057  -0.0337   0.0114   1.0000
  13.750   1.1821   0.09156   0.08489  -0.0346   0.0113   1.0000
  14.000   1.1785   0.09609   0.08959  -0.0359   0.0112   1.0000
  14.250   1.1735   0.10107   0.09474  -0.0377   0.0112   1.0000
  14.500   1.1671   0.10642   0.10027  -0.0400   0.0112   1.0000
  14.750   1.1597   0.11218   0.10621  -0.0427   0.0112   1.0000
  15.000   1.1511   0.11839   0.11259  -0.0459   0.0112   1.0000
  15.250   1.1424   0.12487   0.11926  -0.0495   0.0112   1.0000
  15.500   1.1333   0.13170   0.12626  -0.0535   0.0113   1.0000
  15.750   1.1236   0.13896   0.13368  -0.0578   0.0114   1.0000
  16.000   1.1135   0.14670   0.14157  -0.0625   0.0114   1.0000
  16.250   1.1038   0.15478   0.14980  -0.0675   0.0116   1.0000
  16.500   1.0936   0.16342   0.15857  -0.0728   0.0117   1.0000
  16.750   1.0835   0.17259   0.16785  -0.0783   0.0120   1.0000
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