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GOE 222 (MVA H.33) AIRFOIL (goe222-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 222 (MVA H.33) AIRFOIL (goe222-il)
Reynolds number: 100,000
Max Cl/Cd: 42.51 at α=9.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe222-il-100000.txt
Download as CSV file: xf-goe222-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 222 (MVA H.33) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4212   0.07459   0.06985  -0.1083   0.9064   0.0927
  -8.250  -0.4297   0.06990   0.06503  -0.1105   0.9029   0.0917
  -8.000  -0.4316   0.06381   0.05864  -0.1159   0.8990   0.0905
  -7.750  -0.4090   0.05684   0.05105  -0.1257   0.8956   0.0894
  -7.500  -0.3674   0.05201   0.04551  -0.1345   0.8922   0.0901
  -7.250  -0.3112   0.04871   0.04145  -0.1431   0.8893   0.0919
  -7.000  -0.3024   0.04753   0.03997  -0.1419   0.8830   0.0924
  -6.750  -0.2676   0.04560   0.03793  -0.1444   0.8781   0.0938
  -6.500  -0.2175   0.04413   0.03640  -0.1487   0.8740   0.0966
  -6.250  -0.1994   0.04351   0.03569  -0.1480   0.8661   0.0992
  -6.000  -0.1575   0.04249   0.03444  -0.1508   0.8603   0.1032
  -5.750  -0.1042   0.04121   0.03320  -0.1551   0.8568   0.1078
  -5.500  -0.0956   0.04112   0.03316  -0.1528   0.8482   0.1107
  -5.250  -0.0533   0.04041   0.03239  -0.1555   0.8434   0.1185
  -5.000   0.0007   0.03935   0.03145  -0.1603   0.8405   0.1338
  -4.750   0.0136   0.03927   0.03149  -0.1593   0.8315   0.1487
  -4.500   0.0620   0.03884   0.03176  -0.1638   0.8269   0.2724
  -4.250   0.1037   0.04014   0.03300  -0.1644   0.8234   0.3114
  -4.000   0.1046   0.04134   0.03420  -0.1604   0.8122   0.3225
  -3.750   0.1437   0.04207   0.03487  -0.1609   0.8082   0.3422
  -3.500   0.1496   0.04323   0.03614  -0.1571   0.7975   0.3499
  -3.250   0.1866   0.04354   0.03638  -0.1576   0.7927   0.3657
  -3.000   0.2011   0.04443   0.03732  -0.1551   0.7835   0.3751
  -2.750   0.2305   0.04473   0.03760  -0.1546   0.7773   0.3875
  -2.500   0.2689   0.04482   0.03769  -0.1547   0.7742   0.4046
  -2.250   0.2789   0.04566   0.03848  -0.1525   0.7619   0.4157
  -2.000   0.3155   0.04532   0.03817  -0.1524   0.7582   0.4267
  -1.750   0.3399   0.04545   0.03808  -0.1535   0.7473   0.4376
  -1.500   0.3718   0.04505   0.03775  -0.1528   0.7424   0.4448
  -1.250   0.4222   0.04392   0.03641  -0.1566   0.7400   0.4572
  -1.000   0.4307   0.04472   0.03724  -0.1542   0.7271   0.4611
  -0.750   0.4752   0.04375   0.03614  -0.1566   0.7238   0.4692
  -0.500   0.5256   0.04240   0.03461  -0.1602   0.7221   0.4768
  -0.250   0.5340   0.04334   0.03556  -0.1581   0.7081   0.4801
   0.000   0.5800   0.04212   0.03423  -0.1605   0.7058   0.4875
   0.250   0.6316   0.04057   0.03250  -0.1640   0.7045   0.4948
   0.500   0.6791   0.03905   0.03094  -0.1661   0.7035   0.5002
   0.750   0.6822   0.04052   0.03240  -0.1635   0.6883   0.5044
   1.000   0.6947   0.04171   0.03352  -0.1625   0.6761   0.5098
   1.250   0.7333   0.04080   0.03257  -0.1638   0.6726   0.5157
   1.500   0.7785   0.03951   0.03123  -0.1658   0.6709   0.5221
   1.750   0.8292   0.03812   0.02970  -0.1689   0.6695   0.5306
   2.000   0.8785   0.03667   0.02825  -0.1715   0.6682   0.5383
   2.250   0.9383   0.03522   0.02666  -0.1763   0.6671   0.5484
   2.500   0.9203   0.03743   0.02895  -0.1702   0.6519   0.5509
   2.750   0.9723   0.03600   0.02750  -0.1733   0.6506   0.5599
   3.000   0.9516   0.03911   0.03065  -0.1678   0.6358   0.5637
   3.250   0.9673   0.04006   0.03164  -0.1667   0.6289   0.5704
   3.500   1.0381   0.03733   0.02882  -0.1719   0.6311   0.5844
   3.750   0.9766   0.04388   0.03549  -0.1628   0.6111   0.5839
   4.000   1.0429   0.04069   0.03231  -0.1664   0.6129   0.5970
   4.250   1.1209   0.03712   0.02869  -0.1721   0.6146   0.6144
   4.500   1.0467   0.04477   0.03649  -0.1618   0.5954   0.6120
   4.750   1.1161   0.04110   0.03281  -0.1655   0.5963   0.6310
   5.000   1.2040   0.03673   0.02837  -0.1721   0.5980   0.6556
   5.250   1.1719   0.04049   0.03226  -0.1653   0.5856   0.6613
   5.500   1.2375   0.03753   0.02932  -0.1692   0.5845   0.6910
   5.750   1.3085   0.03454   0.02644  -0.1743   0.5829   0.7348
   6.000   1.2564   0.03911   0.03123  -0.1646   0.5698   0.7468
   6.250   1.3113   0.03608   0.02844  -0.1667   0.5681   1.0000
   6.500   1.3859   0.03400   0.02612  -0.1733   0.5661   1.0000
   6.750   1.3128   0.04009   0.03242  -0.1614   0.5533   1.0000
   7.000   1.3801   0.03772   0.02991  -0.1659   0.5517   1.0000
   7.250   1.4578   0.03527   0.02729  -0.1723   0.5496   1.0000
   7.500   1.3696   0.04236   0.03463  -0.1590   0.5367   1.0000
   7.750   1.4510   0.03883   0.03097  -0.1646   0.5350   1.0000
   8.000   1.3612   0.04739   0.03976  -0.1530   0.5209   1.0000
   8.250   1.4490   0.04261   0.03486  -0.1583   0.5200   1.0000
   8.500   1.5388   0.03889   0.03100  -0.1652   0.5174   1.0000
   8.750   1.3272   0.05801   0.05056  -0.1443   0.4929   1.0000
   9.000   1.3836   0.05470   0.04722  -0.1455   0.4909   1.0000
   9.250   1.6412   0.03861   0.03068  -0.1677   0.4983   1.0000
   9.500   1.2745   0.07214   0.06489  -0.1371   0.4569   1.0000
   9.750   1.6591   0.04051   0.03270  -0.1628   0.4823   1.0000
  10.000   1.5811   0.04657   0.03903  -0.1510   0.4714   1.0000
  10.250   1.6823   0.04222   0.03449  -0.1587   0.4655   1.0000
  10.500   1.6221   0.04728   0.03980  -0.1491   0.4549   1.0000
  10.750   1.7126   0.04364   0.03598  -0.1556   0.4479   1.0000
  11.000   1.6534   0.04864   0.04122  -0.1463   0.4371   1.0000
  11.250   1.7583   0.04429   0.03662  -0.1542   0.4293   1.0000
  11.500   1.6781   0.05039   0.04303  -0.1429   0.4185   1.0000
  11.750   1.7654   0.04690   0.03933  -0.1486   0.4107   1.0000
  12.000   1.6909   0.05310   0.04583  -0.1387   0.4003   1.0000
  12.250   1.7685   0.04993   0.04248  -0.1431   0.3932   1.0000
  12.500   1.6862   0.05734   0.05022  -0.1337   0.3833   1.0000
  12.750   1.7812   0.05261   0.04526  -0.1389   0.3774   1.0000
  13.000   1.6528   0.06455   0.05764  -0.1277   0.3672   1.0000
  13.250   1.7218   0.06073   0.05373  -0.1298   0.3625   1.0000
  13.500   1.4440   0.09469   0.08815  -0.1204   0.3416   1.0000
  13.750   1.5119   0.08831   0.08180  -0.1197   0.3413   1.0000
  14.000   1.6100   0.07907   0.07254  -0.1203   0.3413   1.0000
  14.250   1.4719   0.10019   0.09384  -0.1186   0.3275   1.0000
  14.500   1.5461   0.09283   0.08652  -0.1177   0.3277   1.0000
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