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GOE 228 (MVA H.38) AIRFOIL (goe228-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 228 (MVA H.38) AIRFOIL (goe228-il)
Reynolds number: 50,000
Max Cl/Cd: 25.88 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe228-il-50000-n5.txt
Download as CSV file: xf-goe228-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 228 (MVA H.38) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.1237   0.11354   0.10672  -0.0828   0.9334   0.0836
  -9.500  -0.1163   0.10930   0.10248  -0.0863   0.9274   0.0842
  -9.250  -0.1127   0.10525   0.09842  -0.0892   0.9207   0.0848
  -9.000  -0.1126   0.10135   0.09453  -0.0914   0.9125   0.0851
  -8.750  -0.1056   0.09627   0.08943  -0.0960   0.9076   0.0850
  -8.500  -0.1163   0.09309   0.08631  -0.0958   0.8963   0.0847
  -8.250  -0.1203   0.08822   0.08144  -0.0989   0.8889   0.0845
  -8.000  -0.1378   0.08394   0.07721  -0.0996   0.8776   0.0844
  -7.500  -0.1851   0.06395   0.05692  -0.1201   0.8549   0.0843
  -7.250  -0.1814   0.05576   0.04811  -0.1313   0.8443   0.0860
  -7.000  -0.1420   0.04941   0.04088  -0.1421   0.8402   0.0887
  -6.750  -0.1292   0.04801   0.03940  -0.1413   0.8289   0.0902
  -6.500  -0.0910   0.04586   0.03705  -0.1448   0.8244   0.0937
  -6.250  -0.0689   0.04426   0.03515  -0.1459   0.8147   0.0976
  -6.000  -0.0323   0.04228   0.03285  -0.1488   0.8088   0.1023
  -5.750   0.0094   0.04068   0.03114  -0.1517   0.8052   0.1075
  -5.500   0.0268   0.03992   0.03015  -0.1510   0.7934   0.1129
  -5.250   0.0665   0.03861   0.02883  -0.1534   0.7888   0.1216
  -5.000   0.0889   0.03794   0.02802  -0.1534   0.7786   0.1299
  -4.750   0.1264   0.03681   0.02682  -0.1555   0.7726   0.1441
  -4.500   0.1704   0.03553   0.02562  -0.1587   0.7689   0.1654
  -4.250   0.1873   0.03539   0.02560  -0.1578   0.7564   0.1847
  -4.000   0.2297   0.03458   0.02494  -0.1603   0.7520   0.2260
  -3.750   0.2484   0.03488   0.02529  -0.1593   0.7399   0.2597
  -3.500   0.2869   0.03464   0.02498  -0.1605   0.7349   0.2999
  -3.250   0.3053   0.03505   0.02530  -0.1592   0.7232   0.3245
  -3.000   0.3429   0.03470   0.02476  -0.1603   0.7179   0.3525
  -2.750   0.3609   0.03512   0.02512  -0.1589   0.7067   0.3717
  -2.500   0.3935   0.03497   0.02494  -0.1588   0.7011   0.3973
  -2.250   0.4110   0.03540   0.02535  -0.1571   0.6902   0.4157
  -2.000   0.4447   0.03506   0.02491  -0.1573   0.6846   0.4346
  -1.750   0.4662   0.03527   0.02501  -0.1566   0.6746   0.4477
  -1.500   0.5008   0.03488   0.02444  -0.1575   0.6684   0.4628
  -1.250   0.5230   0.03502   0.02455  -0.1563   0.6598   0.4726
  -1.000   0.5537   0.03483   0.02421  -0.1567   0.6524   0.4848
  -0.750   0.5942   0.03417   0.02336  -0.1582   0.6483   0.4974
  -0.500   0.6082   0.03484   0.02400  -0.1566   0.6369   0.5054
  -0.250   0.6488   0.03424   0.02317  -0.1583   0.6322   0.5185
   0.000   0.6635   0.03490   0.02383  -0.1567   0.6219   0.5263
   0.250   0.6998   0.03454   0.02330  -0.1578   0.6165   0.5393
   0.500   0.7218   0.03493   0.02362  -0.1572   0.6083   0.5501
   0.750   0.7493   0.03503   0.02363  -0.1572   0.6013   0.5622
   1.000   0.7888   0.03452   0.02296  -0.1586   0.5970   0.5777
   1.250   0.7993   0.03562   0.02406  -0.1569   0.5869   0.5905
   1.500   0.8327   0.03542   0.02377  -0.1575   0.5818   0.6065
   1.750   0.8562   0.03579   0.02410  -0.1571   0.5752   0.6225
   2.000   0.8729   0.03648   0.02480  -0.1559   0.5675   0.6387
   2.250   0.9090   0.03620   0.02442  -0.1569   0.5631   0.6607
   2.500   0.9197   0.03725   0.02552  -0.1550   0.5556   0.6788
   2.750   0.9376   0.03784   0.02616  -0.1538   0.5493   0.6998
   3.000   0.9718   0.03755   0.02585  -0.1545   0.5454   0.7276
   3.250   0.9771   0.03882   0.02723  -0.1519   0.5384   0.7514
   3.500   0.9873   0.03975   0.02829  -0.1498   0.5319   0.7829
   3.750   1.0116   0.03934   0.02801  -0.1486   0.5282   0.8478
   4.000   1.0196   0.04063   0.02931  -0.1468   0.5222   1.0000
   4.250   1.0194   0.04316   0.03185  -0.1450   0.5145   1.0000
   4.500   1.0511   0.04355   0.03210  -0.1459   0.5111   1.0000
   4.750   1.0910   0.04338   0.03177  -0.1475   0.5087   1.0000
   5.000   1.0410   0.04977   0.03839  -0.1419   0.4967   1.0000
   5.250   1.0689   0.05024   0.03875  -0.1422   0.4935   1.0000
   5.500   1.1045   0.05008   0.03848  -0.1430   0.4914   1.0000
   6.000   1.0583   0.06049   0.04909  -0.1381   0.4748   1.0000
   6.250   1.0874   0.06075   0.04928  -0.1382   0.4731   1.0000
   6.750   1.0119   0.07686   0.06566  -0.1355   0.4532   1.0000
   7.250   0.9842   0.08810   0.07703  -0.1350   0.4409   1.0000
   7.750   0.9631   0.09834   0.08737  -0.1348   0.4309   1.0000
   8.250   0.9759   0.10437   0.09346  -0.1347   0.4247   1.0000
   8.500   0.9909   0.10639   0.09549  -0.1346   0.4228   1.0000
   8.750   1.0122   0.10758   0.09668  -0.1344   0.4212   1.0000
   9.000   0.9763   0.11550   0.10472  -0.1349   0.4136   1.0000
   9.250   0.9857   0.11785   0.10711  -0.1347   0.4094   1.0000
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