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GOE 228 (MVA H.38) AIRFOIL (goe228-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 228 (MVA H.38) AIRFOIL (goe228-il)
Reynolds number: 100,000
Max Cl/Cd: 45.61 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe228-il-100000.txt
Download as CSV file: xf-goe228-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.0987   0.11024   0.10574  -0.0878   0.9242   0.1591
  -8.500  -0.0410   0.10489   0.10030  -0.0891   0.9231   0.1639
  -8.250  -0.0400   0.10313   0.09855  -0.0896   0.9129   0.1711
  -8.000  -0.0360   0.09928   0.09471  -0.0946   0.9068   0.1766
  -7.750   0.0087   0.09496   0.09032  -0.0985   0.9051   0.1828
  -7.250  -0.1881   0.05527   0.04980  -0.1372   0.8608   0.1000
  -7.000  -0.1472   0.04876   0.04279  -0.1461   0.8566   0.0989
  -6.750  -0.1112   0.04441   0.03776  -0.1523   0.8494   0.0996
  -6.500  -0.0746   0.04117   0.03409  -0.1565   0.8421   0.1018
  -6.250  -0.0254   0.03858   0.03128  -0.1611   0.8388   0.1048
  -6.000   0.0044   0.03710   0.02957  -0.1623   0.8299   0.1074
  -5.750   0.0487   0.03535   0.02738  -0.1656   0.8241   0.1126
  -5.500   0.0997   0.03325   0.02529  -0.1696   0.8216   0.1193
  -5.250   0.1292   0.03235   0.02421  -0.1700   0.8125   0.1257
  -5.000   0.1702   0.03091   0.02283  -0.1721   0.8069   0.1368
  -4.750   0.2183   0.02924   0.02116  -0.1752   0.8040   0.1549
  -4.500   0.2467   0.02848   0.02049  -0.1755   0.7944   0.1761
  -4.250   0.2882   0.02736   0.01963  -0.1777   0.7888   0.2165
  -4.000   0.3342   0.02679   0.01924  -0.1800   0.7853   0.2873
  -3.750   0.3561   0.02734   0.01975  -0.1786   0.7733   0.3292
  -3.500   0.3946   0.02709   0.01954  -0.1791   0.7687   0.3621
  -3.250   0.4189   0.02722   0.01959  -0.1781   0.7581   0.3840
  -3.000   0.4557   0.02673   0.01904  -0.1787   0.7522   0.4051
  -2.750   0.4833   0.02661   0.01889  -0.1781   0.7433   0.4209
  -2.500   0.5144   0.02629   0.01857  -0.1778   0.7355   0.4368
  -2.250   0.5447   0.02609   0.01834  -0.1774   0.7278   0.4528
  -2.000   0.5727   0.02594   0.01815  -0.1768   0.7186   0.4680
  -1.750   0.6045   0.02567   0.01778  -0.1770   0.7109   0.4830
  -1.500   0.6331   0.02550   0.01754  -0.1767   0.7015   0.4954
  -1.250   0.6631   0.02527   0.01724  -0.1767   0.6934   0.5057
  -1.000   0.6949   0.02500   0.01680  -0.1774   0.6844   0.5180
  -0.750   0.7226   0.02489   0.01667  -0.1769   0.6758   0.5271
  -0.500   0.7546   0.02463   0.01626  -0.1776   0.6671   0.5382
  -0.250   0.7826   0.02459   0.01616  -0.1775   0.6585   0.5472
   0.000   0.8134   0.02445   0.01590  -0.1780   0.6501   0.5580
   0.250   0.8423   0.02446   0.01583  -0.1782   0.6418   0.5688
   0.500   0.8708   0.02442   0.01571  -0.1783   0.6333   0.5790
   0.750   0.9010   0.02446   0.01563  -0.1788   0.6255   0.5924
   1.000   0.9267   0.02459   0.01575  -0.1784   0.6170   0.6049
   1.250   0.9594   0.02454   0.01557  -0.1792   0.6106   0.6188
   1.500   0.9803   0.02493   0.01602  -0.1783   0.6018   0.6329
   1.750   1.0137   0.02487   0.01584  -0.1792   0.5960   0.6514
   2.000   1.0335   0.02535   0.01640  -0.1781   0.5880   0.6694
   2.250   1.0612   0.02546   0.01647  -0.1781   0.5814   0.6914
   2.500   1.0913   0.02555   0.01650  -0.1785   0.5758   0.7161
   2.750   1.1080   0.02604   0.01712  -0.1769   0.5681   0.7406
   3.000   1.1361   0.02605   0.01710  -0.1768   0.5628   0.7717
   3.250   1.1592   0.02630   0.01741  -0.1760   0.5576   0.8061
   3.500   1.1711   0.02676   0.01809  -0.1734   0.5513   0.8478
   3.750   1.1950   0.02677   0.01818  -0.1728   0.5465   1.0000
   4.000   1.2379   0.02714   0.01829  -0.1760   0.5426   1.0000
   4.250   1.2497   0.02848   0.01977  -0.1746   0.5362   1.0000
   4.500   1.2758   0.02919   0.02042  -0.1750   0.5310   1.0000
   4.750   1.3110   0.02950   0.02058  -0.1765   0.5269   1.0000
   5.000   1.3297   0.03053   0.02163  -0.1757   0.5217   1.0000
   5.250   1.3439   0.03164   0.02280  -0.1742   0.5160   1.0000
   5.500   1.3723   0.03213   0.02323  -0.1747   0.5117   1.0000
   5.750   1.4100   0.03235   0.02328  -0.1764   0.5082   1.0000
   6.000   1.4102   0.03413   0.02527  -0.1730   0.5031   1.0000
   6.250   1.4203   0.03548   0.02671  -0.1710   0.4983   1.0000
   6.500   1.4456   0.03612   0.02734  -0.1710   0.4946   1.0000
   6.750   1.4818   0.03636   0.02748  -0.1724   0.4917   1.0000
   7.000   1.4872   0.03812   0.02936  -0.1699   0.4880   1.0000
   7.250   1.4539   0.04171   0.03325  -0.1626   0.4828   1.0000
   7.500   1.4569   0.04340   0.03501  -0.1598   0.4789   1.0000
   7.750   1.4943   0.04341   0.03499  -0.1613   0.4760   1.0000
   8.000   1.5463   0.04290   0.03438  -0.1646   0.4737   1.0000
  10.000   0.8943   0.14562   0.13864  -0.1466   0.4621   1.0000
  10.250   0.9379   0.14676   0.13978  -0.1465   0.4570   1.0000
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