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GOE 432 AIRFOIL (goe432-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 432 AIRFOIL (goe432-il)
Reynolds number: 200,000
Max Cl/Cd: 72.55 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe432-il-200000.txt
Download as CSV file: xf-goe432-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 432 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3617   0.08847   0.08514  -0.0209   1.0000   0.0383
  -7.250  -0.3680   0.08651   0.08325  -0.0194   1.0000   0.0388
  -7.000  -0.3713   0.08419   0.08098  -0.0189   1.0000   0.0395
  -6.750  -0.3725   0.08156   0.07839  -0.0191   1.0000   0.0404
  -6.500  -0.3723   0.07882   0.07568  -0.0199   1.0000   0.0414
  -6.250  -0.3698   0.07585   0.07274  -0.0216   1.0000   0.0426
  -6.000  -0.3568   0.07227   0.06910  -0.0293   1.0000   0.0446
  -5.750  -0.3410   0.06840   0.06511  -0.0347   1.0000   0.0451
  -5.500  -0.3313   0.06352   0.06014  -0.0370   1.0000   0.0454
  -5.250  -0.3318   0.05928   0.05600  -0.0347   1.0000   0.0463
  -5.000  -0.3260   0.05701   0.05377  -0.0327   1.0000   0.0473
  -4.750  -0.3173   0.05501   0.05177  -0.0314   1.0000   0.0490
  -4.500  -0.2952   0.05183   0.04851  -0.0339   0.9988   0.0524
  -4.250  -0.2369   0.04373   0.03981  -0.0461   0.9942   0.0588
  -4.000  -0.2057   0.04074   0.03685  -0.0488   0.9889   0.0611
  -3.750  -0.1490   0.03878   0.03408  -0.0552   0.9837   0.0713
  -3.500  -0.1237   0.03330   0.02885  -0.0578   0.9779   0.0753
  -3.250  -0.0821   0.03058   0.02584  -0.0617   0.9727   0.0890
  -3.000  -0.0445   0.02824   0.02321  -0.0644   0.9667   0.1031
  -2.750   0.0008   0.02175   0.01522  -0.0644   0.9623   0.0579
  -2.500   0.0405   0.01875   0.01181  -0.0666   0.9584   0.0594
  -2.250   0.0771   0.01763   0.01063  -0.0683   0.9516   0.0653
  -2.000   0.1173   0.01656   0.00928  -0.0701   0.9452   0.0699
  -1.750   0.1593   0.01526   0.00792  -0.0726   0.9399   0.0763
  -1.500   0.1976   0.01444   0.00706  -0.0741   0.9305   0.0821
  -1.250   0.2367   0.01349   0.00611  -0.0757   0.9216   0.0881
  -1.000   0.2784   0.01269   0.00537  -0.0779   0.9132   0.0966
  -0.750   0.3110   0.01199   0.00473  -0.0783   0.8994   0.1064
  -0.500   0.3445   0.01135   0.00413  -0.0787   0.8827   0.1231
  -0.250   0.4078   0.00854   0.00381  -0.0860   0.8675   1.0000
   0.000   0.4450   0.00836   0.00338  -0.0871   0.8406   1.0000
   0.250   0.4783   0.00831   0.00308  -0.0875   0.8062   1.0000
   0.500   0.5076   0.00840   0.00289  -0.0872   0.7664   1.0000
   0.750   0.5327   0.00860   0.00281  -0.0861   0.7229   1.0000
   1.000   0.5561   0.00886   0.00278  -0.0847   0.6800   1.0000
   1.250   0.5789   0.00914   0.00279  -0.0834   0.6413   1.0000
   1.500   0.6019   0.00944   0.00284  -0.0821   0.6090   1.0000
   1.750   0.6253   0.00974   0.00293  -0.0810   0.5838   1.0000
   2.000   0.6491   0.01004   0.00304  -0.0800   0.5624   1.0000
   2.250   0.6733   0.01034   0.00318  -0.0791   0.5447   1.0000
   2.500   0.6977   0.01064   0.00334  -0.0783   0.5285   1.0000
   2.750   0.7222   0.01091   0.00353  -0.0775   0.5129   1.0000
   3.000   0.7467   0.01118   0.00370  -0.0767   0.4984   1.0000
   3.250   0.7715   0.01142   0.00389  -0.0760   0.4848   1.0000
   3.500   0.7962   0.01165   0.00409  -0.0752   0.4716   1.0000
   3.750   0.8209   0.01187   0.00431  -0.0745   0.4587   1.0000
   4.000   0.8454   0.01210   0.00451  -0.0737   0.4455   1.0000
   4.250   0.8695   0.01231   0.00470  -0.0729   0.4306   1.0000
   4.500   0.8933   0.01252   0.00488  -0.0720   0.4140   1.0000
   4.750   0.9167   0.01275   0.00509  -0.0711   0.3967   1.0000
   5.000   0.9398   0.01301   0.00531  -0.0701   0.3781   1.0000
   5.250   0.9627   0.01327   0.00555  -0.0691   0.3555   1.0000
   5.500   0.9848   0.01362   0.00582  -0.0679   0.3304   1.0000
   5.750   1.0062   0.01405   0.00617  -0.0667   0.3036   1.0000
   6.000   1.0279   0.01451   0.00654  -0.0656   0.2790   1.0000
   6.250   1.0497   0.01501   0.00694  -0.0645   0.2609   1.0000
   6.500   1.0718   0.01550   0.00739  -0.0635   0.2470   1.0000
   6.750   1.0943   0.01598   0.00787  -0.0626   0.2361   1.0000
   7.000   1.1169   0.01647   0.00839  -0.0616   0.2271   1.0000
   7.250   1.1385   0.01709   0.00894  -0.0606   0.2195   1.0000
   7.500   1.1613   0.01758   0.00955  -0.0598   0.2119   1.0000
   7.750   1.1830   0.01829   0.01022  -0.0588   0.2049   1.0000
   8.000   1.2047   0.01884   0.01086  -0.0578   0.1964   1.0000
   8.250   1.2247   0.01948   0.01151  -0.0567   0.1850   1.0000
   8.500   1.2436   0.02014   0.01217  -0.0554   0.1730   1.0000
   8.750   1.2625   0.02092   0.01293  -0.0542   0.1628   1.0000
   9.000   1.2820   0.02130   0.01351  -0.0530   0.1537   1.0000
   9.250   1.3006   0.02185   0.01416  -0.0516   0.1448   1.0000
   9.500   1.3187   0.02225   0.01464  -0.0502   0.1352   1.0000
   9.750   1.3387   0.02234   0.01497  -0.0490   0.1224   1.0000
  10.000   1.3582   0.02256   0.01518  -0.0478   0.0921   1.0000
  10.250   1.3607   0.02450   0.01680  -0.0444   0.0533   1.0000
  10.500   1.3621   0.02625   0.01846  -0.0407   0.0422   1.0000
  10.750   1.3648   0.02769   0.02001  -0.0372   0.0377   1.0000
  11.000   1.3645   0.02932   0.02171  -0.0337   0.0345   1.0000
  11.250   1.3582   0.03141   0.02386  -0.0298   0.0325   1.0000
  11.500   1.3610   0.03301   0.02564  -0.0272   0.0308   1.0000
  11.750   1.3606   0.03495   0.02774  -0.0247   0.0294   1.0000
  12.000   1.3596   0.03707   0.02997  -0.0225   0.0284   1.0000
  12.250   1.3570   0.03948   0.03248  -0.0207   0.0273   1.0000
  12.500   1.3537   0.04218   0.03527  -0.0192   0.0266   1.0000
  12.750   1.3502   0.04519   0.03836  -0.0179   0.0258   1.0000
  13.000   1.3483   0.04852   0.04178  -0.0166   0.0250   1.0000
  13.250   1.3481   0.05124   0.04471  -0.0162   0.0244   1.0000
  13.500   1.3470   0.05426   0.04792  -0.0160   0.0238   1.0000
  13.750   1.3446   0.05757   0.05140  -0.0160   0.0230   1.0000
  14.000   1.3420   0.06111   0.05512  -0.0162   0.0226   1.0000
  14.250   1.3381   0.06493   0.05910  -0.0167   0.0222   1.0000
  14.500   1.3326   0.06909   0.06345  -0.0176   0.0219   1.0000
  14.750   1.3255   0.07360   0.06815  -0.0189   0.0217   1.0000
  15.000   1.3163   0.07859   0.07334  -0.0206   0.0216   1.0000
  15.250   1.3053   0.08400   0.07896  -0.0228   0.0214   1.0000
  15.500   1.2928   0.08988   0.08504  -0.0255   0.0214   1.0000
  15.750   1.2783   0.09637   0.09174  -0.0287   0.0214   1.0000
  16.000   1.2612   0.10361   0.09920  -0.0328   0.0215   1.0000
  16.250   1.2418   0.11167   0.10745  -0.0375   0.0216   1.0000
  16.500   1.2205   0.12062   0.11661  -0.0431   0.0219   1.0000
  16.750   1.1968   0.13066   0.12685  -0.0495   0.0222   1.0000
  17.000   1.1690   0.14242   0.13881  -0.0573   0.0227   1.0000
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