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GOE 421 AIRFOIL (goe421-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 421 AIRFOIL (goe421-il)
Reynolds number: 200,000
Max Cl/Cd: 68.19 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe421-il-200000.txt
Download as CSV file: xf-goe421-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 421 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.0030   0.05932   0.05519  -0.1728   0.8793   0.0747
  -9.750  -0.1408   0.04033   0.03538  -0.1858   0.8601   0.0718
  -9.500  -0.1609   0.03846   0.03322  -0.1813   0.8486   0.0722
  -9.250  -0.1454   0.03505   0.02923  -0.1832   0.8455   0.0735
  -9.000  -0.1179   0.03225   0.02610  -0.1856   0.8438   0.0751
  -8.750  -0.1173   0.03186   0.02571  -0.1814   0.8344   0.0761
  -8.500  -0.0884   0.03067   0.02442  -0.1824   0.8314   0.0781
  -8.250  -0.0558   0.02915   0.02267  -0.1842   0.8294   0.0803
  -8.000  -0.0212   0.02764   0.02079  -0.1862   0.8277   0.0825
  -7.750   0.0146   0.02601   0.01900  -0.1885   0.8263   0.0851
  -7.500   0.0125   0.02607   0.01909  -0.1834   0.8161   0.0864
  -7.250   0.0472   0.02510   0.01801  -0.1849   0.8136   0.0895
  -7.000   0.0844   0.02409   0.01677  -0.1869   0.8116   0.0926
  -6.750   0.1217   0.02289   0.01549  -0.1891   0.8099   0.0963
  -6.500   0.1271   0.02298   0.01563  -0.1852   0.8018   0.0987
  -6.250   0.1566   0.02240   0.01494  -0.1857   0.7981   0.1030
  -6.000   0.1921   0.02147   0.01396  -0.1873   0.7956   0.1078
  -5.750   0.2302   0.02076   0.01320  -0.1894   0.7935   0.1146
  -5.500   0.2546   0.02038   0.01283  -0.1890   0.7892   0.1210
  -5.250   0.2683   0.02041   0.01286  -0.1866   0.7825   0.1275
  -5.000   0.3017   0.01995   0.01243  -0.1877   0.7794   0.1392
  -4.750   0.3395   0.01963   0.01211  -0.1896   0.7770   0.1563
  -4.500   0.3802   0.01957   0.01200  -0.1919   0.7749   0.1765
  -4.250   0.3836   0.02026   0.01270  -0.1874   0.7669   0.1879
  -4.000   0.4139   0.02035   0.01276  -0.1879   0.7631   0.2031
  -3.750   0.4499   0.02023   0.01261  -0.1894   0.7604   0.2171
  -3.500   0.4898   0.02001   0.01228  -0.1917   0.7581   0.2303
  -3.250   0.4978   0.02046   0.01278  -0.1882   0.7509   0.2376
  -3.000   0.5269   0.02028   0.01251  -0.1884   0.7461   0.2470
  -2.750   0.5659   0.01993   0.01211  -0.1904   0.7427   0.2569
  -2.500   0.6012   0.01967   0.01172  -0.1918   0.7386   0.2655
  -2.250   0.6130   0.01982   0.01196  -0.1888   0.7311   0.2712
  -2.000   0.6483   0.01956   0.01156  -0.1901   0.7265   0.2800
  -1.750   0.6905   0.01910   0.01103  -0.1928   0.7231   0.2880
  -1.500   0.6995   0.01935   0.01134  -0.1894   0.7158   0.2926
  -1.250   0.7278   0.01926   0.01117  -0.1895   0.7110   0.2989
  -1.000   0.7645   0.01897   0.01083  -0.1912   0.7076   0.3059
  -0.750   0.7917   0.01897   0.01083  -0.1912   0.7032   0.3122
  -0.500   0.8071   0.01912   0.01098  -0.1889   0.6971   0.3161
  -0.250   0.8379   0.01899   0.01075  -0.1895   0.6928   0.3201
   0.000   0.8753   0.01870   0.01044  -0.1914   0.6895   0.3256
   0.250   0.8932   0.01886   0.01065  -0.1897   0.6841   0.3306
   0.500   0.9133   0.01893   0.01072  -0.1884   0.6784   0.3360
   0.750   0.9467   0.01872   0.01048  -0.1895   0.6742   0.3426
   1.000   0.9840   0.01854   0.01026  -0.1913   0.6703   0.3514
   1.250   0.9912   0.01883   0.01062  -0.1876   0.6632   0.3587
   1.500   1.0200   0.01867   0.01051  -0.1878   0.6580   0.3703
   1.750   1.0588   0.01842   0.01024  -0.1900   0.6539   0.3901
   2.000   1.0662   0.01865   0.01063  -0.1863   0.6468   0.4083
   2.250   1.0919   0.01851   0.01061  -0.1860   0.6411   0.4420
   2.500   1.1289   0.01816   0.01040  -0.1879   0.6367   0.5010
   2.750   1.1349   0.01824   0.01084  -0.1840   0.6294   0.5744
   3.000   1.1555   0.01755   0.01083  -0.1821   0.6234   1.0000
   3.250   1.1915   0.01753   0.01063  -0.1837   0.6182   1.0000
   3.500   1.1919   0.01791   0.01105  -0.1787   0.6101   1.0000
   3.750   1.2200   0.01793   0.01094  -0.1788   0.6038   1.0000
   4.000   1.2327   0.01824   0.01123  -0.1762   0.5962   1.0000
   4.250   1.2501   0.01843   0.01136  -0.1744   0.5884   1.0000
   4.500   1.2703   0.01863   0.01149  -0.1732   0.5808   1.0000
   4.750   1.2811   0.01897   0.01181  -0.1703   0.5717   1.0000
   5.000   1.2991   0.01922   0.01200  -0.1687   0.5630   1.0000
   5.250   1.3117   0.01957   0.01231  -0.1663   0.5532   1.0000
   5.500   1.3226   0.02004   0.01275  -0.1636   0.5428   1.0000
   5.750   1.3436   0.02026   0.01285  -0.1626   0.5333   1.0000
   6.000   1.3477   0.02099   0.01360  -0.1590   0.5214   1.0000
   6.250   1.3623   0.02148   0.01401  -0.1571   0.5109   1.0000
   6.500   1.3770   0.02199   0.01443  -0.1553   0.5005   1.0000
   6.750   1.3864   0.02276   0.01518  -0.1528   0.4894   1.0000
   7.000   1.4055   0.02322   0.01551  -0.1517   0.4805   1.0000
   7.250   1.4149   0.02406   0.01635  -0.1493   0.4707   1.0000
   7.500   1.4353   0.02455   0.01672  -0.1486   0.4632   1.0000
   7.750   1.4459   0.02542   0.01761  -0.1465   0.4550   1.0000
   8.000   1.4694   0.02582   0.01788  -0.1462   0.4489   1.0000
   8.250   1.4814   0.02668   0.01878  -0.1444   0.4422   1.0000
   8.500   1.4966   0.02741   0.01949  -0.1430   0.4360   1.0000
   8.750   1.5235   0.02772   0.01966  -0.1433   0.4306   1.0000
   9.000   1.5304   0.02879   0.02083  -0.1409   0.4250   1.0000
   9.250   1.5450   0.02956   0.02162  -0.1396   0.4197   1.0000
   9.500   1.5705   0.02992   0.02188  -0.1397   0.4154   1.0000
   9.750   1.5865   0.03070   0.02269  -0.1386   0.4112   1.0000
  10.000   1.5977   0.03167   0.02374  -0.1369   0.4071   1.0000
  10.250   1.6148   0.03239   0.02450  -0.1361   0.4035   1.0000
  10.500   1.6365   0.03292   0.02500  -0.1358   0.4002   1.0000
  10.750   1.6688   0.03307   0.02506  -0.1368   0.3967   1.0000
  11.000   1.6717   0.03440   0.02655  -0.1342   0.3933   1.0000
  11.250   1.6817   0.03546   0.02772  -0.1325   0.3899   1.0000
  11.500   1.6966   0.03630   0.02860  -0.1315   0.3866   1.0000
  11.750   1.7161   0.03688   0.02918  -0.1310   0.3831   1.0000
  12.000   1.7414   0.03726   0.02951  -0.1312   0.3791   1.0000
  12.250   1.7379   0.03900   0.03142  -0.1281   0.3754   1.0000
  12.500   1.7422   0.04037   0.03289  -0.1260   0.3712   1.0000
  12.750   1.7550   0.04124   0.03376  -0.1249   0.3668   1.0000
  13.000   1.7800   0.04151   0.03397  -0.1250   0.3623   1.0000
  13.250   1.7713   0.04375   0.03641  -0.1218   0.3586   1.0000
  13.500   1.7713   0.04552   0.03829  -0.1196   0.3541   1.0000
  13.750   1.7824   0.04655   0.03933  -0.1185   0.3497   1.0000
  14.000   1.8056   0.04683   0.03956  -0.1184   0.3454   1.0000
  14.250   1.7959   0.04945   0.04240  -0.1156   0.3420   1.0000
  14.500   1.7933   0.05163   0.04472  -0.1136   0.3378   1.0000
  14.750   1.7996   0.05309   0.04621  -0.1123   0.3330   1.0000
  15.000   1.8139   0.05392   0.04701  -0.1115   0.3280   1.0000
  15.250   1.7981   0.05742   0.05073  -0.1090   0.3234   1.0000
  15.500   1.7952   0.05986   0.05328  -0.1074   0.3183   1.0000
  15.750   1.8131   0.06030   0.05363  -0.1069   0.3129   1.0000
  16.000   1.7978   0.06413   0.05769  -0.1049   0.3086   1.0000
  16.250   1.7879   0.06755   0.06127  -0.1034   0.3035   1.0000
  16.500   1.7940   0.06925   0.06296  -0.1026   0.2976   1.0000
  16.750   1.7820   0.07306   0.06694  -0.1013   0.2920   1.0000
  17.000   1.7675   0.07728   0.07134  -0.1001   0.2857   1.0000
  17.250   1.7707   0.07944   0.07346  -0.0994   0.2789   1.0000
  17.500   1.7472   0.08505   0.07933  -0.0985   0.2721   1.0000
  17.750   1.7440   0.08811   0.08240  -0.0980   0.2641   1.0000
  18.000   1.7188   0.09422   0.08875  -0.0974   0.2557   1.0000
  18.250   1.7049   0.09886   0.09347  -0.0972   0.2461   1.0000
  18.500   1.6851   0.10440   0.09910  -0.0971   0.2345   1.0000
  18.750   1.6618   0.11055   0.10533  -0.0973   0.2203   1.0000
  19.000   1.6402   0.11648   0.11126  -0.0978   0.2031   1.0000
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