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GOE 121 (MVA H.1) AIRFOIL (goe121-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 121 (MVA H.1) AIRFOIL (goe121-il)
Reynolds number: 100,000
Max Cl/Cd: 60.9 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe121-il-100000.txt
Download as CSV file: xf-goe121-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 121 (MVA H.1) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3482   0.10102   0.09597  -0.0205   1.0000   0.0791
  -7.750  -0.3525   0.10016   0.09521  -0.0224   1.0000   0.0815
  -7.500  -0.3581   0.10053   0.09571  -0.0292   1.0000   0.0824
  -7.250  -0.3535   0.09689   0.09213  -0.0317   1.0000   0.0831
  -7.000  -0.3436   0.09123   0.08648  -0.0251   1.0000   0.0846
  -6.750  -0.3364   0.08805   0.08333  -0.0237   1.0000   0.0864
  -6.500  -0.3312   0.08544   0.08076  -0.0237   1.0000   0.0887
  -6.250  -0.3269   0.08303   0.07841  -0.0248   1.0000   0.0913
  -6.000  -0.3204   0.08154   0.07695  -0.0305   1.0000   0.0949
  -5.750  -0.3085   0.07934   0.07471  -0.0385   1.0000   0.0964
  -5.500  -0.3105   0.07545   0.07093  -0.0322   1.0000   0.0976
  -5.250  -0.3077   0.07283   0.06836  -0.0292   1.0000   0.0996
  -5.000  -0.3012   0.07045   0.06599  -0.0289   1.0000   0.1023
  -4.750  -0.2595   0.06921   0.06440  -0.0446   1.0000   0.1096
  -4.500  -0.2594   0.06491   0.06024  -0.0409   1.0000   0.1104
  -4.250  -0.2551   0.06192   0.05732  -0.0382   1.0000   0.1117
  -4.000  -0.2450   0.05944   0.05484  -0.0373   1.0000   0.1142
  -3.500  -0.1982   0.05388   0.04907  -0.0443   1.0000   0.1260
  -3.250  -0.1587   0.05285   0.04766  -0.0508   1.0000   0.1378
  -3.000  -0.1458   0.04890   0.04381  -0.0504   1.0000   0.1395
  -2.750  -0.1300   0.04651   0.04147  -0.0500   1.0000   0.1428
  -2.500  -0.0859   0.04383   0.03854  -0.0562   0.9972   0.1552
  -2.250  -0.0362   0.04111   0.03565  -0.0626   0.9912   0.1701
  -2.000   0.0127   0.03857   0.03306  -0.0682   0.9841   0.1900
  -1.750   0.0722   0.03733   0.03146  -0.0757   0.9741   0.2280
  -1.500   0.1606   0.02792   0.02052  -0.0869   0.9725   0.1078
  -1.250   0.2093   0.02544   0.01764  -0.0911   0.9645   0.1051
  -1.000   0.2619   0.02369   0.01530  -0.0957   0.9588   0.1103
  -0.750   0.3033   0.02228   0.01382  -0.0984   0.9497   0.1150
  -0.500   0.3538   0.02083   0.01207  -0.1023   0.9436   0.1252
  -0.250   0.3960   0.01974   0.01102  -0.1048   0.9338   0.1507
   0.000   0.4399   0.01891   0.01035  -0.1077   0.9247   0.1918
   0.250   0.4880   0.01846   0.01003  -0.1113   0.9165   0.2335
   0.500   0.5272   0.01792   0.00952  -0.1128   0.9038   0.2560
   0.750   0.5649   0.01725   0.00892  -0.1136   0.8901   0.2723
   1.000   0.6004   0.01659   0.00837  -0.1139   0.8748   0.2982
   1.250   0.6333   0.01573   0.00783  -0.1139   0.8584   0.3634
   1.500   0.6591   0.01414   0.00730  -0.1118   0.8413   1.0000
   1.750   0.6849   0.01409   0.00709  -0.1104   0.8191   1.0000
   2.000   0.7125   0.01395   0.00683  -0.1092   0.7980   1.0000
   2.250   0.7386   0.01390   0.00666  -0.1078   0.7739   1.0000
   2.500   0.7655   0.01388   0.00648  -0.1066   0.7500   1.0000
   2.750   0.7913   0.01397   0.00643  -0.1053   0.7230   1.0000
   3.000   0.8163   0.01415   0.00649  -0.1040   0.6942   1.0000
   3.250   0.8411   0.01434   0.00656  -0.1027   0.6644   1.0000
   3.500   0.8657   0.01454   0.00664  -0.1016   0.6345   1.0000
   3.750   0.8903   0.01475   0.00675  -0.1004   0.6056   1.0000
   4.000   0.9152   0.01505   0.00689  -0.0994   0.5795   1.0000
   4.250   0.9403   0.01544   0.00711  -0.0985   0.5574   1.0000
   4.500   0.9653   0.01591   0.00749  -0.0978   0.5355   1.0000
   4.750   0.9904   0.01643   0.00794  -0.0971   0.5158   1.0000
   5.000   1.0156   0.01698   0.00842  -0.0964   0.4981   1.0000
   5.250   1.0409   0.01753   0.00895  -0.0958   0.4817   1.0000
   5.500   1.0659   0.01807   0.00949  -0.0951   0.4652   1.0000
   5.750   1.0892   0.01848   0.01001  -0.0941   0.4442   1.0000
   6.000   1.1116   0.01881   0.01029  -0.0929   0.4209   1.0000
   6.250   1.1331   0.01910   0.01064  -0.0917   0.3951   1.0000
   6.500   1.1550   0.01948   0.01104  -0.0905   0.3719   1.0000
   6.750   1.1765   0.01989   0.01151  -0.0892   0.3481   1.0000
   7.000   1.1959   0.02029   0.01191  -0.0877   0.3162   1.0000
   7.250   1.2152   0.02071   0.01240  -0.0862   0.2732   1.0000
   7.500   1.2238   0.02248   0.01340  -0.0835   0.1536   1.0000
   7.750   1.2278   0.02553   0.01564  -0.0804   0.0817   1.0000
   8.000   1.2384   0.02749   0.01770  -0.0778   0.0713   1.0000
   8.250   1.2481   0.02942   0.01973  -0.0751   0.0661   1.0000
   8.500   1.2620   0.03097   0.02138  -0.0729   0.0612   1.0000
   8.750   1.2733   0.03299   0.02330  -0.0708   0.0569   1.0000
   9.000   1.2910   0.03465   0.02507  -0.0690   0.0541   1.0000
   9.250   1.3114   0.03658   0.02708  -0.0677   0.0521   1.0000
   9.500   1.3341   0.03876   0.02939  -0.0667   0.0504   1.0000
   9.750   1.3567   0.04114   0.03186  -0.0658   0.0489   1.0000
  10.000   1.3808   0.04441   0.03510  -0.0656   0.0468   1.0000
  10.250   1.3974   0.04748   0.03848  -0.0642   0.0458   1.0000
  10.500   1.4115   0.05081   0.04217  -0.0625   0.0457   1.0000
  10.750   1.4217   0.05454   0.04627  -0.0606   0.0458   1.0000
  11.000   1.4289   0.05880   0.05087  -0.0586   0.0461   1.0000
  11.250   1.4341   0.06284   0.05529  -0.0566   0.0466   1.0000
  11.500   1.4279   0.06512   0.05805  -0.0529   0.0474   1.0000
  11.750   1.4031   0.06821   0.06166  -0.0481   0.0484   1.0000
  12.000   1.3741   0.07197   0.06583  -0.0445   0.0493   1.0000
  12.250   1.3464   0.07652   0.07072  -0.0427   0.0500   1.0000
  12.500   1.3189   0.08175   0.07622  -0.0427   0.0507   1.0000
  12.750   1.2911   0.08775   0.08247  -0.0441   0.0512   1.0000
  13.000   1.2623   0.09466   0.08961  -0.0472   0.0517   1.0000
  13.250   1.2320   0.10275   0.09790  -0.0520   0.0522   1.0000
  13.500   1.1996   0.11253   0.10784  -0.0587   0.0527   1.0000
  13.750   1.1662   0.12411   0.11955  -0.0669   0.0535   1.0000
  14.000   1.1407   0.13541   0.13089  -0.0742   0.0548   1.0000
  14.250   1.1413   0.14046   0.13591  -0.0744   0.0562   1.0000
  14.500   0.8598   0.14912   0.14478  -0.0656   0.0669   1.0000
  14.750   0.8672   0.15140   0.14708  -0.0645   0.0681   1.0000
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