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GOE 239 (MVA H.31) AIRFOIL (goe239-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 239 (MVA H.31) AIRFOIL (goe239-il)
Reynolds number: 100,000
Max Cl/Cd: 60.72 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe239-il-100000-n5.txt
Download as CSV file: xf-goe239-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 239 (MVA H.31) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2721   0.11369   0.10884  -0.0375   1.0000   0.0608
  -9.250  -0.2781   0.11197   0.10718  -0.0358   1.0000   0.0613
  -9.000  -0.2845   0.11044   0.10572  -0.0338   1.0000   0.0624
  -8.750  -0.2797   0.10713   0.10242  -0.0422   0.9926   0.0677
  -8.500  -0.2722   0.10297   0.09827  -0.0495   0.9848   0.0682
  -8.250  -0.2480   0.09641   0.09163  -0.0480   0.9832   0.0538
  -8.000  -0.2369   0.09154   0.08675  -0.0528   0.9756   0.0510
  -7.750  -0.2259   0.08741   0.08262  -0.0570   0.9666   0.0511
  -7.500  -0.2104   0.08330   0.07850  -0.0620   0.9588   0.0524
  -7.250  -0.1944   0.07850   0.07368  -0.0681   0.9511   0.0523
  -7.000  -0.1786   0.07320   0.06836  -0.0750   0.9431   0.0515
  -6.750  -0.1567   0.06744   0.06253  -0.0834   0.9362   0.0515
  -6.500  -0.1345   0.06206   0.05709  -0.0914   0.9280   0.0531
  -6.250  -0.1032   0.05369   0.04855  -0.1045   0.9211   0.0536
  -6.000  -0.0566   0.03730   0.03122  -0.1284   0.9141   0.0541
  -5.750  -0.0171   0.03156   0.02450  -0.1363   0.9081   0.0565
  -5.500   0.0218   0.02848   0.02079  -0.1404   0.9039   0.0575
  -5.250   0.0522   0.02675   0.01885  -0.1418   0.8968   0.0587
  -5.000   0.0854   0.02541   0.01732  -0.1434   0.8902   0.0604
  -4.750   0.1198   0.02426   0.01594  -0.1449   0.8841   0.0633
  -4.500   0.1498   0.02316   0.01456  -0.1455   0.8753   0.0655
  -4.250   0.1851   0.02199   0.01310  -0.1469   0.8694   0.0674
  -4.000   0.2126   0.02113   0.01210  -0.1468   0.8592   0.0693
  -3.750   0.2441   0.02034   0.01129  -0.1474   0.8512   0.0722
  -3.500   0.2731   0.01978   0.01065  -0.1475   0.8407   0.0766
  -3.250   0.3021   0.01925   0.00996  -0.1474   0.8296   0.0810
  -3.000   0.3327   0.01856   0.00928  -0.1478   0.8196   0.0858
  -2.750   0.3614   0.01810   0.00873  -0.1478   0.8072   0.0928
  -2.500   0.3900   0.01760   0.00821  -0.1478   0.7940   0.1033
  -2.250   0.4191   0.01709   0.00770  -0.1480   0.7802   0.1184
  -2.000   0.4480   0.01659   0.00739  -0.1481   0.7657   0.1512
  -1.750   0.4766   0.01639   0.00728  -0.1480   0.7506   0.2175
  -1.500   0.5049   0.01634   0.00721  -0.1478   0.7351   0.2577
  -1.250   0.5331   0.01634   0.00714  -0.1475   0.7194   0.2865
  -1.000   0.5614   0.01639   0.00708  -0.1473   0.7040   0.3119
  -0.750   0.5895   0.01644   0.00703  -0.1471   0.6896   0.3330
  -0.500   0.6177   0.01648   0.00695  -0.1469   0.6765   0.3501
  -0.250   0.6456   0.01651   0.00687  -0.1466   0.6639   0.3655
   0.000   0.6731   0.01655   0.00683  -0.1464   0.6521   0.3816
   0.250   0.7008   0.01658   0.00677  -0.1462   0.6417   0.3962
   0.500   0.7286   0.01663   0.00670  -0.1460   0.6318   0.4095
   0.750   0.7560   0.01668   0.00671  -0.1457   0.6220   0.4225
   1.000   0.7836   0.01674   0.00669  -0.1455   0.6135   0.4378
   1.250   0.8106   0.01680   0.00678  -0.1453   0.6042   0.4570
   1.500   0.8379   0.01685   0.00686  -0.1451   0.5964   0.4841
   1.750   0.8643   0.01684   0.00703  -0.1448   0.5877   0.5351
   2.000   0.8840   0.01616   0.00701  -0.1426   0.5807   1.0000
   2.250   0.9111   0.01644   0.00720  -0.1424   0.5722   1.0000
   2.500   0.9389   0.01674   0.00732  -0.1423   0.5650   1.0000
   2.750   0.9654   0.01703   0.00758  -0.1420   0.5567   1.0000
   3.000   0.9928   0.01734   0.00776  -0.1419   0.5498   1.0000
   3.250   1.0191   0.01765   0.00805  -0.1416   0.5422   1.0000
   3.500   1.0458   0.01796   0.00831  -0.1414   0.5352   1.0000
   3.750   1.0723   0.01829   0.00860  -0.1411   0.5284   1.0000
   4.000   1.0983   0.01862   0.00893  -0.1408   0.5210   1.0000
   4.250   1.1253   0.01896   0.00921  -0.1406   0.5149   1.0000
   4.500   1.1502   0.01931   0.00963  -0.1401   0.5073   1.0000
   4.750   1.1762   0.01965   0.00996  -0.1398   0.5007   1.0000
   5.000   1.2012   0.02001   0.01038  -0.1393   0.4934   1.0000
   5.250   1.2261   0.02035   0.01076  -0.1388   0.4856   1.0000
   5.500   1.2510   0.02071   0.01115  -0.1383   0.4783   1.0000
   5.750   1.2749   0.02107   0.01161  -0.1377   0.4701   1.0000
   6.000   1.2996   0.02143   0.01200  -0.1371   0.4631   1.0000
   6.250   1.3226   0.02182   0.01251  -0.1364   0.4546   1.0000
   6.500   1.3468   0.02218   0.01290  -0.1357   0.4476   1.0000
   6.750   1.3689   0.02259   0.01348  -0.1348   0.4385   1.0000
   7.000   1.3916   0.02296   0.01390  -0.1340   0.4302   1.0000
   7.250   1.4128   0.02334   0.01438  -0.1329   0.4200   1.0000
   7.500   1.4331   0.02373   0.01490  -0.1316   0.4089   1.0000
   7.750   1.4530   0.02411   0.01533  -0.1303   0.3980   1.0000
   8.000   1.4722   0.02450   0.01576  -0.1289   0.3871   1.0000
   8.250   1.4905   0.02500   0.01637  -0.1274   0.3757   1.0000
   8.500   1.5081   0.02551   0.01697  -0.1258   0.3646   1.0000
   8.750   1.5242   0.02606   0.01755  -0.1239   0.3530   1.0000
   9.000   1.5389   0.02666   0.01817  -0.1219   0.3413   1.0000
   9.250   1.5531   0.02735   0.01897  -0.1199   0.3301   1.0000
   9.500   1.5665   0.02807   0.01978  -0.1178   0.3202   1.0000
   9.750   1.5763   0.02884   0.02058  -0.1151   0.3103   1.0000
  10.000   1.5851   0.02971   0.02158  -0.1124   0.2992   1.0000
  10.250   1.5929   0.03068   0.02264  -0.1098   0.2883   1.0000
  10.500   1.5996   0.03175   0.02378  -0.1071   0.2778   1.0000
  10.750   1.6054   0.03295   0.02509  -0.1045   0.2665   1.0000
  11.000   1.6089   0.03434   0.02660  -0.1019   0.2536   1.0000
  11.250   1.6093   0.03601   0.02835  -0.0992   0.2386   1.0000
  11.500   1.6068   0.03801   0.03040  -0.0966   0.2213   1.0000
  12.000   1.5928   0.04332   0.03572  -0.0919   0.1741   1.0000
  12.250   1.5781   0.04702   0.03930  -0.0898   0.1454   1.0000
  12.500   1.5602   0.05137   0.04352  -0.0882   0.1273   1.0000
  12.750   1.5439   0.05588   0.04801  -0.0872   0.1147   1.0000
  13.000   1.5280   0.06064   0.05278  -0.0866   0.1054   1.0000
  13.250   1.5159   0.06523   0.05746  -0.0863   0.0960   1.0000
  13.500   1.5035   0.07003   0.06235  -0.0864   0.0883   1.0000
  13.750   1.4904   0.07512   0.06753  -0.0868   0.0815   1.0000
  14.000   1.4784   0.08019   0.07269  -0.0874   0.0761   1.0000
  14.250   1.4650   0.08556   0.07813  -0.0881   0.0718   1.0000
  14.500   1.4517   0.09098   0.08363  -0.0890   0.0684   1.0000
  14.750   1.4403   0.09622   0.08900  -0.0900   0.0649   1.0000
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