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GOE 532 AIRFOIL (goe532-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 532 AIRFOIL (goe532-il)
Reynolds number: 500,000
Max Cl/Cd: 101.71 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe532-il-500000.txt
Download as CSV file: xf-goe532-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 532 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2876   0.09998   0.09760  -0.0348   1.0000   0.0328
  -9.750  -0.2854   0.09705   0.09470  -0.0355   1.0000   0.0337
  -9.500  -0.3205   0.08768   0.08538  -0.0438   1.0000   0.0355
  -9.250  -0.3160   0.08556   0.08329  -0.0420   1.0000   0.0358
  -9.000  -0.3122   0.08392   0.08169  -0.0405   1.0000   0.0359
  -8.750  -0.3094   0.08264   0.08046  -0.0387   1.0000   0.0362
  -8.500  -0.2863   0.07967   0.07749  -0.0425   0.9967   0.0368
  -8.250  -0.2951   0.05493   0.05241  -0.0855   0.9680   0.0407
  -8.000  -0.2727   0.05190   0.04952  -0.0858   0.9608   0.0411
  -7.750  -0.2423   0.05037   0.04801  -0.0883   0.9533   0.0415
  -7.500  -0.2113   0.04764   0.04523  -0.0933   0.9417   0.0421
  -7.250  -0.1976   0.03902   0.03566  -0.1054   0.9144   0.0465
  -7.000  -0.1813   0.03408   0.03063  -0.1070   0.8965   0.0474
  -6.750  -0.1588   0.03257   0.02908  -0.1071   0.8789   0.0480
  -6.500  -0.1378   0.03112   0.02752  -0.1070   0.8614   0.0487
  -6.250  -0.1176   0.02948   0.02568  -0.1068   0.8442   0.0500
  -6.000  -0.1015   0.02661   0.02211  -0.1065   0.8269   0.0543
  -5.750  -0.0789   0.02508   0.02055  -0.1061   0.8099   0.0551
  -5.500  -0.0560   0.02394   0.01930  -0.1056   0.7911   0.0562
  -5.250  -0.0363   0.01797   0.01194  -0.1036   0.7744   0.0408
  -5.000  -0.0114   0.01707   0.01083  -0.1028   0.7520   0.0406
  -4.750   0.0131   0.01604   0.00960  -0.1020   0.7277   0.0406
  -4.250   0.0623   0.01434   0.00747  -0.1003   0.6753   0.0410
  -4.000   0.0872   0.01360   0.00663  -0.0997   0.6533   0.0417
  -3.750   0.1128   0.01321   0.00613  -0.0990   0.6345   0.0424
  -3.500   0.1388   0.01284   0.00566  -0.0984   0.6190   0.0429
  -3.250   0.1648   0.01251   0.00523  -0.0978   0.6047   0.0435
  -3.000   0.1911   0.01220   0.00485  -0.0973   0.5908   0.0441
  -2.750   0.2177   0.01192   0.00450  -0.0968   0.5778   0.0448
  -2.500   0.2442   0.01170   0.00420  -0.0963   0.5666   0.0456
  -2.250   0.2711   0.01151   0.00394  -0.0958   0.5564   0.0464
  -2.000   0.2976   0.01116   0.00357  -0.0954   0.5477   0.0479
  -1.750   0.3245   0.01098   0.00337  -0.0950   0.5389   0.0496
  -1.500   0.3516   0.01085   0.00320  -0.0946   0.5313   0.0513
  -1.250   0.3791   0.01074   0.00305  -0.0943   0.5236   0.0530
  -1.000   0.4059   0.01059   0.00285  -0.0939   0.5163   0.0559
  -0.750   0.4336   0.01047   0.00273  -0.0936   0.5088   0.0600
  -0.500   0.4608   0.01037   0.00260  -0.0933   0.5020   0.0690
  -0.250   0.4857   0.00953   0.00251  -0.0930   0.4962   0.3011
   0.000   0.5118   0.00922   0.00258  -0.0927   0.4904   0.4341
   0.250   0.5380   0.00911   0.00264  -0.0922   0.4849   0.5114
   0.500   0.5641   0.00900   0.00272  -0.0917   0.4798   0.5850
   0.750   0.5899   0.00886   0.00281  -0.0910   0.4740   0.6632
   1.000   0.6146   0.00876   0.00288  -0.0901   0.4684   0.7367
   1.250   0.6580   0.00832   0.00292  -0.0929   0.4625   1.0000
   1.500   0.6856   0.00840   0.00296  -0.0926   0.4571   1.0000
   1.750   0.7126   0.00852   0.00300  -0.0923   0.4510   1.0000
   2.000   0.7396   0.00864   0.00305  -0.0919   0.4444   1.0000
   2.250   0.7667   0.00873   0.00309  -0.0916   0.4366   1.0000
   2.500   0.7932   0.00888   0.00316  -0.0911   0.4291   1.0000
   2.750   0.8206   0.00896   0.00322  -0.0909   0.4224   1.0000
   3.000   0.8472   0.00910   0.00330  -0.0905   0.4159   1.0000
   3.250   0.8742   0.00922   0.00340  -0.0901   0.4099   1.0000
   3.500   0.9011   0.00933   0.00348  -0.0898   0.4024   1.0000
   3.750   0.9274   0.00948   0.00358  -0.0894   0.3944   1.0000
   4.000   0.9540   0.00960   0.00368  -0.0890   0.3845   1.0000
   4.250   0.9803   0.00975   0.00379  -0.0886   0.3740   1.0000
   4.500   1.0060   0.00993   0.00391  -0.0881   0.3606   1.0000
   4.750   1.0313   0.01014   0.00405  -0.0875   0.3404   1.0000
   5.000   1.0535   0.01058   0.00426  -0.0866   0.2995   1.0000
   5.250   1.0721   0.01135   0.00470  -0.0851   0.2459   1.0000
   5.500   1.0931   0.01192   0.00511  -0.0840   0.2232   1.0000
   5.750   1.1161   0.01233   0.00544  -0.0832   0.2125   1.0000
   6.000   1.1395   0.01268   0.00576  -0.0824   0.2060   1.0000
   6.250   1.1631   0.01300   0.00606  -0.0816   0.2010   1.0000
   6.500   1.1859   0.01336   0.00639  -0.0808   0.1966   1.0000
   6.750   1.2088   0.01370   0.00673  -0.0799   0.1926   1.0000
   7.000   1.2326   0.01397   0.00701  -0.0792   0.1895   1.0000
   7.250   1.2555   0.01428   0.00733  -0.0784   0.1862   1.0000
   7.500   1.2775   0.01463   0.00769  -0.0775   0.1830   1.0000
   7.750   1.2983   0.01505   0.00809  -0.0764   0.1795   1.0000
   8.000   1.3205   0.01536   0.00843  -0.0754   0.1769   1.0000
   8.250   1.3433   0.01561   0.00874  -0.0746   0.1740   1.0000
   8.500   1.3647   0.01594   0.00909  -0.0736   0.1704   1.0000
   8.750   1.3836   0.01638   0.00951  -0.0723   0.1658   1.0000
   9.000   1.4031   0.01676   0.00992  -0.0710   0.1620   1.0000
   9.250   1.4243   0.01700   0.01022  -0.0699   0.1581   1.0000
   9.500   1.4416   0.01738   0.01060  -0.0682   0.1531   1.0000
   9.750   1.4567   0.01784   0.01107  -0.0662   0.1479   1.0000
  10.000   1.4758   0.01814   0.01140  -0.0649   0.1397   1.0000
  10.250   1.4912   0.01861   0.01185  -0.0631   0.1281   1.0000
  10.750   1.5047   0.02047   0.01345  -0.0576   0.0955   1.0000
  11.000   1.5106   0.02151   0.01447  -0.0549   0.0910   1.0000
  11.250   1.5182   0.02250   0.01552  -0.0527   0.0889   1.0000
  11.500   1.5245   0.02365   0.01672  -0.0505   0.0871   1.0000
  11.750   1.5290   0.02498   0.01811  -0.0484   0.0856   1.0000
  12.000   1.5315   0.02656   0.01974  -0.0464   0.0841   1.0000
  12.250   1.5321   0.02840   0.02164  -0.0446   0.0825   1.0000
  12.500   1.5310   0.03051   0.02381  -0.0430   0.0810   1.0000
  12.750   1.5344   0.03239   0.02577  -0.0418   0.0801   1.0000
  13.000   1.5395   0.03421   0.02769  -0.0410   0.0793   1.0000
  13.250   1.5429   0.03627   0.02985  -0.0402   0.0785   1.0000
  13.500   1.5454   0.03851   0.03218  -0.0396   0.0777   1.0000
  13.750   1.5466   0.04096   0.03471  -0.0391   0.0767   1.0000
  14.000   1.5473   0.04352   0.03736  -0.0388   0.0758   1.0000
  14.250   1.5473   0.04621   0.04013  -0.0385   0.0749   1.0000
  14.500   1.5459   0.04910   0.04308  -0.0384   0.0739   1.0000
  14.750   1.5426   0.05222   0.04625  -0.0383   0.0727   1.0000
  15.000   1.5379   0.05540   0.04946  -0.0380   0.0712   1.0000
  15.250   1.5406   0.05800   0.05215  -0.0381   0.0704   1.0000
  15.500   1.5445   0.06060   0.05486  -0.0385   0.0696   1.0000
  15.750   1.5475   0.06331   0.05767  -0.0389   0.0686   1.0000
  16.000   1.5495   0.06619   0.06064  -0.0394   0.0674   1.0000
  16.250   1.5507   0.06917   0.06370  -0.0399   0.0663   1.0000
  16.500   1.5521   0.07215   0.06675  -0.0405   0.0654   1.0000
  16.750   1.5529   0.07524   0.06989  -0.0411   0.0645   1.0000
  17.000   1.5526   0.07844   0.07313  -0.0417   0.0634   1.0000
  17.250   1.5546   0.08109   0.07579  -0.0419   0.0623   1.0000
  17.500   1.5567   0.08408   0.07888  -0.0426   0.0616   1.0000
  17.750   1.5572   0.08755   0.08247  -0.0438   0.0609   1.0000
  18.000   1.5578   0.09099   0.08603  -0.0450   0.0601   1.0000
  18.250   1.5580   0.09450   0.08964  -0.0462   0.0592   1.0000
  18.500   1.5581   0.09804   0.09327  -0.0475   0.0583   1.0000
  18.750   1.5581   0.10161   0.09692  -0.0489   0.0573   1.0000
  19.000   1.5571   0.10542   0.10080  -0.0504   0.0564   1.0000
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