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GOE 226 (MVA H.36) AIRFOIL (goe226-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 226 (MVA H.36) AIRFOIL (goe226-il)
Reynolds number: 200,000
Max Cl/Cd: 78.67 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe226-il-200000-n5.txt
Download as CSV file: xf-goe226-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 226 (MVA H.36) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.0025   0.09281   0.08849  -0.0946   0.8485   0.0409
  -9.250   0.0035   0.08967   0.08533  -0.0962   0.8422   0.0410
  -7.750   0.0051   0.03027   0.02500  -0.1745   0.8024   0.0469
  -7.500   0.0454   0.02574   0.01989  -0.1847   0.7951   0.0482
  -7.250   0.0798   0.02337   0.01705  -0.1892   0.7891   0.0496
  -7.000   0.1124   0.02175   0.01502  -0.1918   0.7834   0.0509
  -6.750   0.1412   0.02101   0.01425  -0.1927   0.7764   0.0519
  -6.500   0.1711   0.02027   0.01339  -0.1937   0.7710   0.0529
  -6.250   0.2013   0.01951   0.01248  -0.1947   0.7656   0.0541
  -6.000   0.2314   0.01877   0.01156  -0.1956   0.7596   0.0555
  -5.750   0.2619   0.01807   0.01062  -0.1965   0.7542   0.0571
  -5.500   0.2916   0.01751   0.00998  -0.1971   0.7485   0.0588
  -5.250   0.3209   0.01713   0.00956  -0.1976   0.7418   0.0605
  -5.000   0.3507   0.01670   0.00901  -0.1981   0.7361   0.0625
  -4.750   0.3804   0.01628   0.00846  -0.1985   0.7299   0.0645
  -4.500   0.4099   0.01590   0.00802  -0.1990   0.7235   0.0666
  -4.250   0.4395   0.01565   0.00770  -0.1993   0.7181   0.0693
  -4.000   0.4688   0.01542   0.00740  -0.1996   0.7121   0.0725
  -3.750   0.4983   0.01516   0.00710  -0.2000   0.7064   0.0755
  -3.500   0.5277   0.01499   0.00685  -0.2002   0.7009   0.0791
  -3.250   0.5567   0.01483   0.00662  -0.2004   0.6938   0.0838
  -3.000   0.5858   0.01467   0.00644  -0.2006   0.6875   0.0885
  -2.750   0.6151   0.01456   0.00621  -0.2008   0.6819   0.0945
  -2.500   0.6440   0.01440   0.00608  -0.2011   0.6756   0.1009
  -2.250   0.6730   0.01433   0.00591  -0.2012   0.6697   0.1080
  -2.000   0.7023   0.01418   0.00574  -0.2015   0.6644   0.1159
  -1.750   0.7309   0.01411   0.00565  -0.2016   0.6584   0.1239
  -1.500   0.7598   0.01402   0.00555  -0.2018   0.6526   0.1330
  -1.250   0.7887   0.01397   0.00546  -0.2020   0.6472   0.1431
  -1.000   0.8170   0.01393   0.00546  -0.2021   0.6408   0.1563
  -0.750   0.8455   0.01389   0.00545  -0.2022   0.6345   0.1763
  -0.500   0.8738   0.01389   0.00549  -0.2023   0.6282   0.2067
  -0.250   0.9014   0.01392   0.00558  -0.2022   0.6207   0.2386
   0.000   0.9291   0.01399   0.00562  -0.2021   0.6136   0.2623
   0.250   0.9564   0.01406   0.00571  -0.2019   0.6059   0.2803
   0.500   0.9836   0.01415   0.00577  -0.2017   0.5981   0.2962
   0.750   1.0106   0.01425   0.00587  -0.2015   0.5902   0.3114
   1.000   1.0372   0.01434   0.00598  -0.2013   0.5812   0.3259
   1.250   1.0635   0.01446   0.00609  -0.2009   0.5721   0.3399
   1.500   1.0894   0.01458   0.00620  -0.2005   0.5615   0.3546
   1.750   1.1151   0.01472   0.00634  -0.2001   0.5496   0.3706
   2.000   1.1403   0.01487   0.00649  -0.1996   0.5370   0.3856
   2.250   1.1651   0.01504   0.00665  -0.1990   0.5240   0.4025
   2.500   1.1894   0.01525   0.00683  -0.1984   0.5110   0.4209
   2.750   1.2133   0.01547   0.00704  -0.1977   0.4983   0.4408
   3.000   1.2367   0.01573   0.00726  -0.1969   0.4870   0.4613
   3.250   1.2593   0.01603   0.00751  -0.1960   0.4771   0.4812
   3.500   1.2825   0.01631   0.00778  -0.1952   0.4677   0.5012
   3.750   1.3046   0.01666   0.00809  -0.1943   0.4589   0.5226
   4.000   1.3268   0.01698   0.00842  -0.1934   0.4501   0.5478
   4.250   1.3481   0.01735   0.00877  -0.1923   0.4428   0.5774
   4.500   1.3711   0.01761   0.00911  -0.1915   0.4371   0.6171
   4.750   1.3936   0.01788   0.00945  -0.1907   0.4322   0.6679
   5.000   1.4146   0.01804   0.00976  -0.1895   0.4278   0.7550
   5.250   1.4334   0.01822   0.01003  -0.1878   0.4238   1.0000
   5.500   1.4562   0.01857   0.01040  -0.1871   0.4196   1.0000
   5.750   1.4784   0.01896   0.01078  -0.1863   0.4155   1.0000
   6.000   1.5001   0.01938   0.01117  -0.1853   0.4118   1.0000
   6.250   1.5214   0.01984   0.01157  -0.1844   0.4084   1.0000
   6.500   1.5424   0.02024   0.01200  -0.1833   0.4052   1.0000
   6.750   1.5626   0.02064   0.01245  -0.1822   0.4016   1.0000
   7.000   1.5823   0.02107   0.01292  -0.1810   0.3978   1.0000
   7.250   1.6017   0.02155   0.01341  -0.1798   0.3939   1.0000
   7.500   1.6214   0.02207   0.01390  -0.1787   0.3902   1.0000
   7.750   1.6403   0.02257   0.01444  -0.1774   0.3866   1.0000
   8.000   1.6579   0.02307   0.01504  -0.1760   0.3827   1.0000
   8.250   1.6755   0.02360   0.01564  -0.1747   0.3788   1.0000
   8.500   1.6924   0.02419   0.01625  -0.1732   0.3748   1.0000
   8.750   1.7092   0.02482   0.01686  -0.1718   0.3705   1.0000
   9.000   1.7228   0.02548   0.01767  -0.1700   0.3652   1.0000
   9.250   1.7361   0.02620   0.01846  -0.1682   0.3597   1.0000
   9.500   1.7493   0.02697   0.01924  -0.1665   0.3547   1.0000
   9.750   1.7623   0.02777   0.02014  -0.1648   0.3494   1.0000
  10.000   1.7736   0.02866   0.02113  -0.1629   0.3431   1.0000
  10.250   1.7836   0.02964   0.02212  -0.1610   0.3372   1.0000
  10.500   1.7946   0.03064   0.02324  -0.1593   0.3306   1.0000
  10.750   1.8042   0.03173   0.02440  -0.1575   0.3244   1.0000
  11.000   1.8136   0.03288   0.02561  -0.1557   0.3186   1.0000
  11.250   1.8221   0.03412   0.02696  -0.1539   0.3113   1.0000
  11.500   1.8278   0.03557   0.02844  -0.1519   0.3040   1.0000
  11.750   1.8338   0.03707   0.03003  -0.1501   0.2952   1.0000
  12.000   1.8373   0.03879   0.03178  -0.1481   0.2870   1.0000
  12.250   1.8391   0.04072   0.03374  -0.1462   0.2774   1.0000
  12.500   1.8402   0.04279   0.03585  -0.1443   0.2677   1.0000
  12.750   1.8384   0.04519   0.03824  -0.1423   0.2583   1.0000
  13.000   1.8381   0.04758   0.04068  -0.1407   0.2482   1.0000
  13.250   1.8366   0.05017   0.04329  -0.1390   0.2392   1.0000
  13.500   1.8345   0.05289   0.04604  -0.1375   0.2306   1.0000
  13.750   1.8343   0.05550   0.04871  -0.1362   0.2230   1.0000
  14.000   1.8312   0.05849   0.05175  -0.1349   0.2150   1.0000
  14.250   1.8291   0.06145   0.05478  -0.1338   0.2067   1.0000
  14.500   1.8210   0.06515   0.05849  -0.1326   0.1973   1.0000
  14.750   1.8152   0.06871   0.06211  -0.1317   0.1855   1.0000
  15.000   1.8071   0.07260   0.06605  -0.1308   0.1732   1.0000
  15.250   1.7945   0.07717   0.07063  -0.1301   0.1580   1.0000
  15.500   1.7746   0.08279   0.07621  -0.1296   0.1399   1.0000
  15.750   1.7505   0.08912   0.08249  -0.1294   0.1225   1.0000
  16.000   1.7265   0.09566   0.08900  -0.1295   0.1079   1.0000
  16.250   1.7034   0.10224   0.09558  -0.1299   0.0940   1.0000
  16.500   1.6807   0.10889   0.10223  -0.1306   0.0782   1.0000
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