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GOE 567 AIRFOIL (goe567-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 567 AIRFOIL (goe567-il)
Reynolds number: 200,000
Max Cl/Cd: 80.99 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe567-il-200000.txt
Download as CSV file: xf-goe567-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 567 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.2784   0.11013   0.10668  -0.0500   0.9953   0.0895
 -10.250  -0.3002   0.10158   0.09815  -0.0677   0.9862   0.0970
 -10.000  -0.4665   0.04672   0.04259  -0.1211   0.9562   0.0738
  -9.500  -0.3288   0.06321   0.05965  -0.0992   0.9619   0.0839
  -9.250  -0.3770   0.03909   0.03456  -0.1343   0.9394   0.0823
  -9.000  -0.3626   0.03541   0.03019  -0.1384   0.9271   0.0844
  -8.750  -0.3336   0.03140   0.02599  -0.1424   0.9231   0.0870
  -8.500  -0.3093   0.03047   0.02507  -0.1424   0.9129   0.0893
  -8.250  -0.2767   0.02858   0.02292  -0.1449   0.9078   0.0918
  -8.000  -0.2544   0.02700   0.02102  -0.1452   0.8977   0.0940
  -7.750  -0.2235   0.02560   0.01921  -0.1468   0.8917   0.0964
  -7.500  -0.2010   0.02384   0.01716  -0.1469   0.8822   0.0981
  -7.250  -0.1717   0.02239   0.01565  -0.1478   0.8758   0.1005
  -7.000  -0.1460   0.02165   0.01482  -0.1477   0.8673   0.1030
  -6.750  -0.1174   0.02083   0.01383  -0.1480   0.8601   0.1056
  -6.500  -0.0905   0.02009   0.01289  -0.1480   0.8526   0.1079
  -6.250  -0.0630   0.01953   0.01212  -0.1479   0.8449   0.1102
  -6.000  -0.0356   0.01846   0.01094  -0.1481   0.8384   0.1131
  -5.750  -0.0101   0.01790   0.01038  -0.1478   0.8302   0.1159
  -5.500   0.0191   0.01738   0.00976  -0.1480   0.8242   0.1190
  -5.250   0.0445   0.01702   0.00931  -0.1475   0.8162   0.1223
  -5.000   0.0727   0.01662   0.00877  -0.1475   0.8095   0.1256
  -4.750   0.0989   0.01604   0.00824  -0.1472   0.8027   0.1297
  -4.500   0.1255   0.01572   0.00789  -0.1470   0.7954   0.1339
  -4.250   0.1549   0.01545   0.00750  -0.1471   0.7897   0.1391
  -4.000   0.1794   0.01507   0.00720  -0.1466   0.7818   0.1454
  -3.750   0.2076   0.01481   0.00690  -0.1465   0.7754   0.1533
  -3.500   0.2345   0.01451   0.00664  -0.1464   0.7690   0.1640
  -3.250   0.2610   0.01421   0.00641  -0.1462   0.7617   0.1840
  -3.000   0.2897   0.01378   0.00616  -0.1465   0.7560   0.2351
  -2.750   0.3151   0.01362   0.00622  -0.1461   0.7486   0.2925
  -2.500   0.3430   0.01361   0.00623  -0.1460   0.7421   0.3296
  -2.250   0.3715   0.01369   0.00627  -0.1459   0.7362   0.3578
  -2.000   0.3974   0.01376   0.00638  -0.1454   0.7286   0.3794
  -1.750   0.4263   0.01383   0.00639  -0.1454   0.7228   0.3992
  -1.500   0.4528   0.01393   0.00650  -0.1450   0.7162   0.4161
  -1.250   0.4800   0.01400   0.00655  -0.1447   0.7093   0.4320
  -1.000   0.5094   0.01409   0.00657  -0.1448   0.7040   0.4490
  -0.750   0.5343   0.01421   0.00675  -0.1441   0.6966   0.4654
  -0.500   0.5621   0.01430   0.00681  -0.1439   0.6905   0.4818
  -0.250   0.5906   0.01441   0.00686  -0.1438   0.6851   0.4970
   0.000   0.6156   0.01448   0.00701  -0.1431   0.6778   0.5106
   0.250   0.6437   0.01453   0.00705  -0.1430   0.6721   0.5255
   0.500   0.6706   0.01463   0.00716  -0.1427   0.6664   0.5397
   0.750   0.6966   0.01469   0.00725  -0.1422   0.6596   0.5527
   1.000   0.7255   0.01471   0.00720  -0.1422   0.6542   0.5661
   1.250   0.7507   0.01474   0.00731  -0.1416   0.6471   0.5777
   1.500   0.7776   0.01472   0.00730  -0.1413   0.6404   0.5902
   1.750   0.8057   0.01472   0.00725  -0.1412   0.6344   0.6039
   2.000   0.8303   0.01472   0.00732  -0.1405   0.6264   0.6178
   2.250   0.8587   0.01468   0.00725  -0.1404   0.6204   0.6328
   2.500   0.8834   0.01472   0.00739  -0.1397   0.6138   0.6477
   2.750   0.9097   0.01472   0.00746  -0.1393   0.6077   0.6645
   3.000   0.9384   0.01471   0.00745  -0.1394   0.6029   0.6842
   3.250   0.9613   0.01473   0.00765  -0.1384   0.5962   0.7060
   3.500   0.9864   0.01466   0.00772  -0.1378   0.5905   0.7381
   3.750   1.0102   0.01438   0.00771  -0.1365   0.5859   0.8316
   4.000   1.0400   0.01444   0.00790  -0.1370   0.5787   1.0000
   4.250   1.0685   0.01457   0.00794  -0.1371   0.5724   1.0000
   4.500   1.0938   0.01472   0.00806  -0.1366   0.5647   1.0000
   4.750   1.1197   0.01481   0.00808  -0.1362   0.5564   1.0000
   5.000   1.1444   0.01497   0.00822  -0.1356   0.5483   1.0000
   5.250   1.1696   0.01512   0.00834  -0.1350   0.5407   1.0000
   5.500   1.1951   0.01531   0.00851  -0.1345   0.5337   1.0000
   5.750   1.2187   0.01551   0.00875  -0.1338   0.5263   1.0000
   6.250   1.2673   0.01595   0.00920  -0.1324   0.5125   1.0000
   6.500   1.2925   0.01614   0.00935  -0.1319   0.5054   1.0000
   6.750   1.3139   0.01638   0.00966  -0.1308   0.4973   1.0000
   7.000   1.3373   0.01657   0.00982  -0.1299   0.4892   1.0000
   7.250   1.3577   0.01681   0.01015  -0.1286   0.4807   1.0000
   7.500   1.3801   0.01704   0.01037  -0.1276   0.4730   1.0000
   7.750   1.3997   0.01731   0.01071  -0.1261   0.4646   1.0000
   8.000   1.4205   0.01755   0.01096  -0.1249   0.4563   1.0000
   8.250   1.4382   0.01784   0.01134  -0.1231   0.4473   1.0000
   8.750   1.4719   0.01843   0.01202  -0.1193   0.4280   1.0000
   9.000   1.4866   0.01876   0.01238  -0.1171   0.4183   1.0000
   9.250   1.4977   0.01911   0.01276  -0.1142   0.4074   1.0000
   9.500   1.5063   0.01955   0.01326  -0.1109   0.3949   1.0000
   9.750   1.5155   0.02005   0.01381  -0.1080   0.3829   1.0000
  10.000   1.5233   0.02065   0.01443  -0.1049   0.3699   1.0000
  10.250   1.5286   0.02138   0.01518  -0.1017   0.3545   1.0000
  10.500   1.5315   0.02229   0.01609  -0.0983   0.3361   1.0000
  10.750   1.5304   0.02349   0.01723  -0.0947   0.3146   1.0000
  11.000   1.5258   0.02504   0.01870  -0.0911   0.2899   1.0000
  11.250   1.5166   0.02707   0.02060  -0.0874   0.2636   1.0000
  11.500   1.5059   0.02948   0.02288  -0.0841   0.2366   1.0000
  11.750   1.4948   0.03217   0.02545  -0.0813   0.2114   1.0000
  12.000   1.4826   0.03520   0.02836  -0.0788   0.1882   1.0000
  12.250   1.4735   0.03818   0.03126  -0.0768   0.1682   1.0000
  12.500   1.4643   0.04134   0.03435  -0.0751   0.1530   1.0000
  12.750   1.4564   0.04452   0.03749  -0.0737   0.1422   1.0000
  13.000   1.4478   0.04794   0.04086  -0.0726   0.1336   1.0000
  13.250   1.4440   0.05098   0.04393  -0.0717   0.1255   1.0000
  13.500   1.4355   0.05460   0.04751  -0.0708   0.1192   1.0000
  13.750   1.4365   0.05734   0.05034  -0.0703   0.1126   1.0000
  14.000   1.4327   0.06064   0.05363  -0.0698   0.1070   1.0000
  14.250   1.4338   0.06349   0.05654  -0.0694   0.1017   1.0000
  14.500   1.4365   0.06624   0.05937  -0.0692   0.0965   1.0000
  14.750   1.4357   0.06938   0.06250  -0.0691   0.0925   1.0000
  15.000   1.4415   0.07188   0.06514  -0.0691   0.0881   1.0000
  15.250   1.4455   0.07462   0.06797  -0.0692   0.0841   1.0000
  15.500   1.4458   0.07786   0.07120  -0.0694   0.0808   1.0000
  15.750   1.4510   0.08053   0.07399  -0.0696   0.0771   1.0000
  16.000   1.4530   0.08369   0.07722  -0.0701   0.0734   1.0000
  16.250   1.4518   0.08728   0.08080  -0.0706   0.0702   1.0000
  16.500   1.4534   0.09050   0.08413  -0.0711   0.0666   1.0000
  16.750   1.4511   0.09432   0.08795  -0.0718   0.0632   1.0000
  17.000   1.4496   0.09791   0.09156  -0.0724   0.0597   1.0000
  17.250   1.4474   0.10172   0.09544  -0.0731   0.0558   1.0000
  17.500   1.4455   0.10517   0.09884  -0.0734   0.0516   1.0000
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