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GOE 217 (MVA MK.12) AIRFOIL (goe217-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 217 (MVA MK.12) AIRFOIL (goe217-il)
Reynolds number: 50,000
Max Cl/Cd: 5.03 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe217-il-50000.txt
Download as CSV file: xf-goe217-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 217 (MVA MK.12) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.0942   0.12133   0.11548  -0.0459   0.9517   0.2716
  -8.000  -0.0679   0.11731   0.11144  -0.0509   0.9403   0.2742
  -7.000  -0.1315   0.08956   0.08360  -0.0781   0.8954   0.1576
  -6.750  -0.1480   0.08526   0.07933  -0.0800   0.8803   0.1535
  -6.500  -0.1713   0.05157   0.04432  -0.1326   0.8740   0.1382
  -6.250  -0.1451   0.04904   0.04143  -0.1372   0.8609   0.1395
  -6.000  -0.0857   0.04603   0.03797  -0.1446   0.8537   0.1422
  -5.750  -0.0631   0.04528   0.03699  -0.1453   0.8416   0.1437
  -5.500  -0.0238   0.04456   0.03640  -0.1463   0.8333   0.1472
  -5.250   0.0045   0.04428   0.03611  -0.1468   0.8239   0.1512
  -5.000   0.0312   0.04406   0.03584  -0.1475   0.8142   0.1563
  -4.750   0.0858   0.04306   0.03497  -0.1515   0.8085   0.1691
  -4.500   0.0917   0.04395   0.03604  -0.1504   0.7967   0.1779
  -4.250   0.1419   0.04325   0.03573  -0.1550   0.7894   0.2190
  -4.000   0.1830   0.04443   0.03738  -0.1545   0.7839   0.2935
  -3.750   0.1669   0.04688   0.03987  -0.1509   0.7726   0.3075
  -3.500   0.1858   0.04959   0.04253  -0.1470   0.7661   0.3423
  -3.250   0.1995   0.05286   0.04581  -0.1406   0.7607   0.3648
  -3.000   0.1743   0.05544   0.04848  -0.1357   0.7520   0.3667
  -2.750   0.1817   0.05807   0.05105  -0.1318   0.7462   0.3847
  -2.500   0.1774   0.06128   0.05436  -0.1229   0.7424   0.3933
  -2.250   0.1927   0.06387   0.05689  -0.1172   0.7390   0.4127
  -2.000   0.1784   0.06619   0.05923  -0.1153   0.7353   0.4190
  -1.750   0.1779   0.06827   0.06129  -0.1134   0.7320   0.4296
  -1.500   0.1753   0.07048   0.06351  -0.1096   0.7304   0.4392
  -1.250   0.1819   0.07242   0.06542  -0.1088   0.7307   0.4512
  -1.000   0.1820   0.07450   0.06751  -0.1058   0.7316   0.4620
  -0.750   0.1880   0.07634   0.06933  -0.1045   0.7324   0.4744
  -0.500   0.2056   0.07840   0.07131  -0.1064   0.7343   0.4917
  -0.250   0.2084   0.08029   0.07327  -0.1006   0.7384   0.5058
   0.500   0.1370   0.08874   0.08206  -0.1020   0.8728   0.5032
   0.750   0.1397   0.08833   0.08163  -0.1004   0.8597   0.5165
   1.000   0.1607   0.09084   0.08415  -0.0981   0.8531   0.5409
   1.250   0.1637   0.09126   0.08454  -0.0960   0.8432   0.5542
   1.500   0.1863   0.09256   0.08582  -0.0958   0.8337   0.5704
   1.750   0.2318   0.09541   0.08849  -0.1033   0.8274   0.5797
   2.000   0.2428   0.09518   0.08825  -0.1024   0.8128   0.5846
   2.250   0.3064   0.09969   0.09258  -0.1117   0.8069   0.5986
   2.500   0.2976   0.09826   0.09119  -0.1083   0.7912   0.6027
   2.750   0.3604   0.10292   0.09568  -0.1166   0.7845   0.6182
   3.000   0.3501   0.10157   0.09438  -0.1132   0.7682   0.6224
   3.250   0.3973   0.10547   0.09816  -0.1190   0.7608   0.6379
   3.500   0.4002   0.10511   0.09783  -0.1169   0.7441   0.6455
   3.750   0.4192   0.10722   0.09990  -0.1189   0.7323   0.6567
   4.000   0.4604   0.10989   0.10250  -0.1228   0.7190   0.6725
   4.250   0.4586   0.11057   0.10322  -0.1210   0.7047   0.6796
   4.500   0.5163   0.11483   0.10740  -0.1264   0.6943   0.6989
   4.750   0.5095   0.11518   0.10776  -0.1252   0.6768   0.7053
   5.000   0.5270   0.11764   0.11022  -0.1260   0.6660   0.7164
   5.250   0.5619   0.12011   0.11265  -0.1283   0.6505   0.7307
   5.500   0.5604   0.12172   0.11427  -0.1280   0.6347   0.7375
   5.750   0.6206   0.12698   0.11943  -0.1329   0.6252   0.7553
   6.000   0.6049   0.12672   0.11923  -0.1307   0.6077   0.7589
   6.250   0.6101   0.12917   0.12168  -0.1309   0.5956   0.7662
   6.500   0.6536   0.13266   0.12511  -0.1337   0.5828   0.7789
   6.750   0.6397   0.13416   0.12664  -0.1328   0.5697   0.7824
   7.000   0.7009   0.13929   0.13169  -0.1366   0.5596   0.7968
   7.250   0.6691   0.13960   0.13205  -0.1350   0.5469   0.7972
   7.500   0.7228   0.14454   0.13692  -0.1382   0.5381   0.8103
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