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GOE 222 (MVA H.33) AIRFOIL (goe222-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 222 (MVA H.33) AIRFOIL (goe222-il)
Reynolds number: 50,000
Max Cl/Cd: 5.16 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe222-il-50000.txt
Download as CSV file: xf-goe222-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -6.500  -0.3964   0.13592   0.13059  -0.0029   1.0000   0.2864
  -6.250  -0.4270   0.13573   0.13050  -0.0010   1.0000   0.2896
  -6.000  -0.4631   0.13557   0.13045   0.0016   1.0000   0.2906
  -5.250  -0.5217   0.09158   0.08633  -0.0380   1.0000   0.1627
  -5.000  -0.4994   0.07961   0.07414  -0.0526   1.0000   0.1582
  -4.750  -0.4015   0.05657   0.04929  -0.0949   1.0000   0.1586
  -4.500  -0.3685   0.05442   0.04678  -0.0996   1.0000   0.1645
  -4.250  -0.3437   0.05381   0.04610  -0.1012   1.0000   0.1710
  -4.000  -0.3117   0.05268   0.04467  -0.1047   1.0000   0.1793
  -3.750  -0.2871   0.05268   0.04464  -0.1061   1.0000   0.1907
  -3.500  -0.2652   0.05311   0.04522  -0.1067   1.0000   0.2056
  -3.250  -0.2444   0.05385   0.04614  -0.1070   1.0000   0.2265
  -2.500  -0.1763   0.06486   0.05791  -0.1009   0.9733   0.3476
  -2.250  -0.1606   0.06792   0.06101  -0.0977   0.9656   0.3717
  -2.000  -0.1350   0.07099   0.06402  -0.0967   0.9544   0.4030
  -1.750  -0.1297   0.07218   0.06526  -0.0928   0.9453   0.4223
  -1.500  -0.1002   0.07514   0.06810  -0.0930   0.9375   0.4563
  -1.250  -0.0954   0.07543   0.06840  -0.0900   0.9292   0.4748
  -1.000  -0.0709   0.07736   0.07030  -0.0889   0.9224   0.4974
  -0.750  -0.0546   0.07740   0.07019  -0.0904   0.9165   0.5122
  -0.500  -0.0253   0.07837   0.07104  -0.0920   0.9077   0.5262
  -0.250  -0.0038   0.07927   0.07185  -0.0932   0.9037   0.5380
   0.000   0.0198   0.07964   0.07206  -0.0959   0.8955   0.5501
   0.250   0.0568   0.08135   0.07361  -0.0997   0.8902   0.5631
   0.500   0.0712   0.08192   0.07411  -0.1002   0.8864   0.5710
   0.750   0.0965   0.08266   0.07473  -0.1025   0.8776   0.5798
   1.000   0.1419   0.08522   0.07711  -0.1080   0.8728   0.5902
   1.250   0.1437   0.08501   0.07687  -0.1067   0.8675   0.5948
   1.500   0.1773   0.08654   0.07822  -0.1111   0.8605   0.6023
   1.750   0.2177   0.08922   0.08080  -0.1152   0.8564   0.6109
   2.000   0.2192   0.08900   0.08053  -0.1140   0.8484   0.6150
   2.250   0.2564   0.09110   0.08250  -0.1183   0.8421   0.6220
   2.500   0.2806   0.09310   0.08444  -0.1202   0.8388   0.6289
   2.750   0.2930   0.09369   0.08497  -0.1206   0.8295   0.6346
   3.000   0.3331   0.09646   0.08764  -0.1248   0.8242   0.6424
   3.250   0.3359   0.09691   0.08808  -0.1236   0.8165   0.6468
   3.500   0.3691   0.09917   0.09024  -0.1271   0.8095   0.6554
   3.750   0.3886   0.10117   0.09221  -0.1281   0.8048   0.6627
   4.000   0.4064   0.10238   0.09336  -0.1290   0.7944   0.6702
   4.250   0.4467   0.10591   0.09681  -0.1330   0.7898   0.6801
   4.500   0.4443   0.10589   0.09680  -0.1310   0.7787   0.6858
   4.750   0.4901   0.10981   0.10066  -0.1355   0.7730   0.6993
   5.000   0.4848   0.10968   0.10054  -0.1331   0.7611   0.7056
   5.250   0.5156   0.11270   0.10355  -0.1355   0.7546   0.7180
   5.500   0.5279   0.11371   0.10458  -0.1354   0.7417   0.7284
   5.750   0.5386   0.11556   0.10647  -0.1353   0.7329   0.7403
   6.000   0.5718   0.11811   0.10907  -0.1375   0.7222   0.7602
   6.250   0.5702   0.11920   0.11027  -0.1358   0.7115   0.7727
   6.500   0.6127   0.12265   0.11389  -0.1387   0.7030   0.8083
   6.750   0.5995   0.12281   0.11423  -0.1357   0.6911   0.8307
   7.000   0.6262   0.12553   0.11707  -0.1373   0.6836   1.0000
   7.250   0.6370   0.12725   0.11873  -0.1384   0.6700   1.0000
   7.500   0.6445   0.12981   0.12122  -0.1393   0.6599   1.0000
   7.750   0.6957   0.13473   0.12594  -0.1443   0.6496   1.0000
   8.000   0.6780   0.13545   0.12667  -0.1424   0.6391   1.0000
   8.250   0.7167   0.14015   0.13122  -0.1457   0.6320   1.0000
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