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GOE 442 AIRFOIL (goe442-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 442 AIRFOIL (goe442-il)
Reynolds number: 1,000,000
Max Cl/Cd: 114.97 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe442-il-1000000.txt
Download as CSV file: xf-goe442-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 442 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3672   0.09290   0.09131  -0.0207   1.0000   0.0120
  -8.250  -0.3694   0.09029   0.08873  -0.0202   1.0000   0.0114
  -7.750  -0.3953   0.08525   0.08377  -0.0178   1.0000   0.0132
  -7.500  -0.3787   0.08017   0.07869  -0.0246   0.9975   0.0132
  -7.250  -0.3895   0.01920   0.01601  -0.0810   0.9843   0.0104
  -7.000  -0.3653   0.01668   0.01313  -0.0814   0.9812   0.0108
  -6.750  -0.3360   0.01597   0.01232  -0.0820   0.9784   0.0113
  -6.500  -0.3052   0.01463   0.01076  -0.0830   0.9762   0.0117
  -6.250  -0.2725   0.01350   0.00941  -0.0842   0.9745   0.0123
  -6.000  -0.2387   0.01251   0.00823  -0.0856   0.9732   0.0128
  -5.750  -0.2026   0.01187   0.00744  -0.0873   0.9721   0.0132
  -5.500  -0.1683   0.01046   0.00581  -0.0888   0.9708   0.0142
  -5.250  -0.1429   0.01009   0.00541  -0.0881   0.9650   0.0150
  -5.000  -0.1105   0.00974   0.00502  -0.0888   0.9614   0.0161
  -4.750  -0.0777   0.00946   0.00467  -0.0897   0.9583   0.0170
  -4.500  -0.0502   0.00880   0.00394  -0.0895   0.9532   0.0188
  -4.250  -0.0223   0.00855   0.00368  -0.0892   0.9470   0.0202
  -4.000   0.0094   0.00833   0.00340  -0.0898   0.9422   0.0217
  -3.750   0.0343   0.00794   0.00299  -0.0889   0.9331   0.0241
  -3.500   0.0637   0.00786   0.00290  -0.0890   0.9255   0.0265
  -3.250   0.0912   0.00762   0.00262  -0.0886   0.9147   0.0289
  -3.000   0.1186   0.00747   0.00246  -0.0883   0.9019   0.0319
  -2.750   0.1463   0.00742   0.00237  -0.0879   0.8869   0.0344
  -2.500   0.1731   0.00725   0.00211  -0.0874   0.8683   0.0370
  -2.250   0.1991   0.00715   0.00194  -0.0868   0.8437   0.0400
  -2.000   0.2248   0.00717   0.00186  -0.0860   0.8145   0.0427
  -1.750   0.2499   0.00724   0.00179  -0.0851   0.7828   0.0446
  -1.500   0.2739   0.00717   0.00155  -0.0841   0.7482   0.0476
  -1.250   0.2975   0.00723   0.00144  -0.0830   0.7063   0.0510
  -1.000   0.3210   0.00738   0.00139  -0.0819   0.6540   0.0541
  -0.750   0.3441   0.00761   0.00136  -0.0807   0.5928   0.0565
  -0.500   0.3685   0.00767   0.00125  -0.0799   0.5565   0.0609
  -0.250   0.3942   0.00770   0.00120  -0.0793   0.5342   0.0664
   0.000   0.4204   0.00777   0.00119  -0.0788   0.5170   0.0705
   0.250   0.4465   0.00775   0.00113  -0.0783   0.5015   0.0815
   0.500   0.4718   0.00754   0.00114  -0.0778   0.4878   0.1797
   0.750   0.4969   0.00731   0.00121  -0.0773   0.4752   0.3131
   1.000   0.5202   0.00691   0.00129  -0.0765   0.4624   0.5206
   1.250   0.5843   0.00598   0.00141  -0.0848   0.4427   1.0000
   1.500   0.6095   0.00609   0.00144  -0.0841   0.4303   1.0000
   1.750   0.6347   0.00621   0.00148  -0.0834   0.4162   1.0000
   2.000   0.6598   0.00634   0.00153  -0.0827   0.4024   1.0000
   2.250   0.6850   0.00647   0.00159  -0.0820   0.3900   1.0000
   2.500   0.7101   0.00661   0.00166  -0.0813   0.3779   1.0000
   2.750   0.7355   0.00673   0.00173  -0.0807   0.3662   1.0000
   3.000   0.7607   0.00686   0.00181  -0.0800   0.3548   1.0000
   3.250   0.7858   0.00700   0.00190  -0.0794   0.3434   1.0000
   3.500   0.8108   0.00716   0.00200  -0.0787   0.3309   1.0000
   3.750   0.8357   0.00733   0.00212  -0.0780   0.3171   1.0000
   4.000   0.8605   0.00751   0.00223  -0.0773   0.3028   1.0000
   4.250   0.8853   0.00770   0.00236  -0.0767   0.2873   1.0000
   4.500   0.9098   0.00792   0.00250  -0.0760   0.2678   1.0000
   4.750   0.9333   0.00824   0.00269  -0.0751   0.2393   1.0000
   5.000   0.9547   0.00878   0.00297  -0.0740   0.1915   1.0000
   5.250   0.9766   0.00928   0.00329  -0.0729   0.1577   1.0000
   5.500   1.0002   0.00961   0.00356  -0.0721   0.1438   1.0000
   5.750   1.0241   0.00992   0.00382  -0.0713   0.1352   1.0000
   6.000   1.0489   0.01012   0.00404  -0.0707   0.1316   1.0000
   6.250   1.0733   0.01037   0.00428  -0.0700   0.1276   1.0000
   6.500   1.0969   0.01070   0.00459  -0.0693   0.1218   1.0000
   6.750   1.1218   0.01088   0.00480  -0.0687   0.1193   1.0000
   7.000   1.1464   0.01109   0.00502  -0.0681   0.1153   1.0000
   7.250   1.1700   0.01139   0.00530  -0.0674   0.1104   1.0000
   7.500   1.1939   0.01167   0.00560  -0.0667   0.1069   1.0000
   7.750   1.2189   0.01182   0.00579  -0.0662   0.1040   1.0000
   8.000   1.2429   0.01206   0.00604  -0.0655   0.1002   1.0000
   8.250   1.2660   0.01239   0.00636  -0.0648   0.0951   1.0000
   8.500   1.2906   0.01256   0.00658  -0.0642   0.0914   1.0000
   8.750   1.3138   0.01286   0.00685  -0.0635   0.0835   1.0000
   9.000   1.3358   0.01326   0.00717  -0.0626   0.0700   1.0000
   9.250   1.3482   0.01451   0.00812  -0.0603   0.0317   1.0000
   9.500   1.3641   0.01544   0.00899  -0.0584   0.0193   1.0000
   9.750   1.3829   0.01606   0.00963  -0.0570   0.0161   1.0000
  10.000   1.4008   0.01675   0.01036  -0.0554   0.0136   1.0000
  10.250   1.4198   0.01729   0.01096  -0.0541   0.0125   1.0000
  10.500   1.4369   0.01796   0.01168  -0.0524   0.0115   1.0000
  10.750   1.4501   0.01892   0.01273  -0.0502   0.0104   1.0000
  11.000   1.4668   0.01952   0.01341  -0.0485   0.0100   1.0000
  11.250   1.4821   0.02017   0.01413  -0.0466   0.0095   1.0000
  11.500   1.4943   0.02084   0.01487  -0.0442   0.0091   1.0000
  11.750   1.5044   0.02158   0.01567  -0.0415   0.0087   1.0000
  12.000   1.5124   0.02245   0.01661  -0.0387   0.0082   1.0000
  12.250   1.5167   0.02355   0.01780  -0.0354   0.0079   1.0000
  12.500   1.5117   0.02525   0.01965  -0.0313   0.0075   1.0000
  12.750   1.5209   0.02614   0.02063  -0.0291   0.0073   1.0000
  13.000   1.5281   0.02721   0.02178  -0.0270   0.0071   1.0000
  13.250   1.5304   0.02865   0.02333  -0.0245   0.0070   1.0000
  13.500   1.5340   0.03011   0.02488  -0.0225   0.0068   1.0000
  13.750   1.5357   0.03182   0.02670  -0.0207   0.0066   1.0000
  14.000   1.5360   0.03379   0.02876  -0.0192   0.0064   1.0000
  14.250   1.5322   0.03633   0.03142  -0.0180   0.0064   1.0000
  14.500   1.5291   0.03905   0.03426  -0.0173   0.0062   1.0000
  14.750   1.5280   0.04179   0.03709  -0.0171   0.0060   1.0000
  15.000   1.5198   0.04563   0.04106  -0.0175   0.0060   1.0000
  15.250   1.5124   0.04973   0.04527  -0.0185   0.0059   1.0000
  15.500   1.5030   0.05441   0.05008  -0.0201   0.0058   1.0000
  15.750   1.4890   0.06000   0.05582  -0.0222   0.0058   1.0000
  16.000   1.4723   0.06616   0.06211  -0.0247   0.0057   1.0000
  16.250   1.4557   0.07238   0.06845  -0.0273   0.0056   1.0000
  16.500   1.4386   0.07882   0.07501  -0.0300   0.0056   1.0000
  16.750   1.4189   0.08587   0.08219  -0.0331   0.0056   1.0000
  17.000   1.4013   0.09281   0.08925  -0.0363   0.0056   1.0000
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