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GOE 116 (MVA MK.3) AIRFOIL (goe116-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 116 (MVA MK.3) AIRFOIL (goe116-il)
Reynolds number: 50,000
Max Cl/Cd: 29.59 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe116-il-50000.txt
Download as CSV file: xf-goe116-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 116 (MVA MK.3) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3768   0.11907   0.11246  -0.0243   1.0000   0.1651
  -9.250  -0.3811   0.11723   0.11072  -0.0267   1.0000   0.1675
  -9.000  -0.3902   0.11598   0.10960  -0.0296   1.0000   0.1684
  -8.750  -0.3790   0.11081   0.10447  -0.0299   1.0000   0.1693
  -8.500  -0.3672   0.10611   0.09974  -0.0299   1.0000   0.1707
  -8.250  -0.3606   0.10241   0.09609  -0.0304   1.0000   0.1724
  -8.000  -0.3574   0.09914   0.09290  -0.0312   1.0000   0.1738
  -7.750  -0.3570   0.09615   0.09001  -0.0318   1.0000   0.1750
  -7.500  -0.3601   0.09345   0.08744  -0.0321   1.0000   0.1757
  -7.250  -0.3660   0.09097   0.08511  -0.0320   1.0000   0.1757
  -7.000  -0.3748   0.08873   0.08303  -0.0316   1.0000   0.1748
  -6.750  -0.3896   0.08709   0.08154  -0.0302   1.0000   0.1734
  -6.500  -0.4084   0.08577   0.08035  -0.0290   1.0000   0.1716
  -6.250  -0.4267   0.07769   0.07230  -0.0363   1.0000   0.1120
  -6.000  -0.4335   0.07108   0.06562  -0.0425   1.0000   0.1018
  -5.750  -0.4309   0.06792   0.06244  -0.0419   1.0000   0.1000
  -5.500  -0.4245   0.06335   0.05778  -0.0441   1.0000   0.0973
  -5.250  -0.4031   0.05076   0.04449  -0.0558   1.0000   0.0901
  -5.000  -0.3808   0.04448   0.03769  -0.0596   1.0000   0.0900
  -4.750  -0.3626   0.04290   0.03597  -0.0596   1.0000   0.0940
  -4.500  -0.3307   0.03760   0.02984  -0.0635   1.0000   0.1021
  -4.250  -0.3053   0.03594   0.02782  -0.0642   1.0000   0.1148
  -4.000  -0.2838   0.03560   0.02745  -0.0635   1.0000   0.1325
  -3.750  -0.2580   0.03443   0.02591  -0.0637   1.0000   0.1987
  -3.500  -0.2496   0.03593   0.02774  -0.0608   1.0000   0.2569
  -3.250  -0.2330   0.03597   0.02764  -0.0598   1.0000   0.2948
  -3.000  -0.2149   0.03562   0.02714  -0.0590   1.0000   0.3178
  -2.750  -0.1964   0.03524   0.02667  -0.0585   1.0000   0.3415
  -2.500  -0.1695   0.03457   0.02552  -0.0600   1.0000   0.3496
  -2.250  -0.1462   0.03392   0.02466  -0.0605   1.0000   0.3546
  -2.000  -0.1208   0.03343   0.02383  -0.0616   1.0000   0.3574
  -1.750  -0.0776   0.03311   0.02300  -0.0659   0.9946   0.3614
  -1.500  -0.0395   0.03286   0.02249  -0.0692   0.9884   0.3671
  -1.250   0.0052   0.03285   0.02216  -0.0736   0.9823   0.3711
  -1.000   0.0376   0.03286   0.02192  -0.0757   0.9759   0.3746
  -0.750   0.0795   0.03306   0.02187  -0.0794   0.9696   0.3820
  -0.500   0.1096   0.03331   0.02193  -0.0810   0.9631   0.3892
  -0.250   0.1481   0.03362   0.02211  -0.0840   0.9568   0.3961
   0.000   0.1784   0.03399   0.02238  -0.0855   0.9503   0.4036
   0.250   0.2125   0.03436   0.02272  -0.0877   0.9441   0.4134
   0.500   0.2438   0.03479   0.02319  -0.0894   0.9378   0.4273
   0.750   0.2734   0.03521   0.02373  -0.0909   0.9314   0.4485
   1.000   0.3082   0.03554   0.02438  -0.0933   0.9256   0.4866
   1.250   0.3259   0.03471   0.02499  -0.0917   0.9198   0.7820
   1.500   0.3580   0.03567   0.02558  -0.0936   0.9133   1.0000
   1.750   0.3729   0.03665   0.02634  -0.0926   0.9070   1.0000
   2.000   0.4054   0.03778   0.02726  -0.0945   0.9010   1.0000
   2.250   0.4225   0.03890   0.02829  -0.0940   0.8952   1.0000
   2.500   0.4462   0.04007   0.02937  -0.0947   0.8894   1.0000
   2.750   0.4716   0.04134   0.03057  -0.0957   0.8840   1.0000
   3.000   0.4856   0.04258   0.03180  -0.0950   0.8788   1.0000
   3.250   0.5140   0.04393   0.03315  -0.0964   0.8735   1.0000
   3.500   0.5281   0.04532   0.03460  -0.0959   0.8689   1.0000
   3.750   0.5421   0.04674   0.03606  -0.0954   0.8647   1.0000
   4.000   0.5671   0.04827   0.03765  -0.0965   0.8600   1.0000
   4.250   0.5824   0.04986   0.03930  -0.0963   0.8560   1.0000
   4.500   0.5919   0.05147   0.04099  -0.0954   0.8534   1.0000
   4.750   0.6051   0.05315   0.04277  -0.0951   0.8506   1.0000
   5.000   0.6357   0.05499   0.04480  -0.0971   0.8439   1.0000
   5.250   0.6401   0.05674   0.04666  -0.0957   0.8414   1.0000
   5.500   0.6646   0.05830   0.04839  -0.0963   0.8275   1.0000
   5.750   0.7025   0.05922   0.04957  -0.0973   0.7990   1.0000
   6.000   0.7415   0.05995   0.05064  -0.0980   0.7718   1.0000
   6.250   0.7674   0.06101   0.05199  -0.0978   0.7518   1.0000
   6.500   0.8071   0.06117   0.05255  -0.0976   0.7238   1.0000
   6.750   0.9656   0.03263   0.02155  -0.0659   0.1210   1.0000
   7.000   0.9626   0.03502   0.02375  -0.0626   0.1064   1.0000
   7.250   0.9639   0.03726   0.02598  -0.0599   0.0974   1.0000
   7.500   0.9658   0.03956   0.02827  -0.0573   0.0927   1.0000
   7.750   0.9765   0.04132   0.03016  -0.0547   0.0886   1.0000
   8.000   1.0045   0.04248   0.03132  -0.0521   0.0843   1.0000
   8.250   1.1147   0.04505   0.03404  -0.0565   0.0767   1.0000
   8.500   1.1597   0.04860   0.03794  -0.0572   0.0764   1.0000
   8.750   1.1930   0.05267   0.04239  -0.0569   0.0783   1.0000
   9.000   1.2238   0.05785   0.04777  -0.0568   0.0807   1.0000
   9.250   1.2294   0.06021   0.05106  -0.0531   0.0846   1.0000
   9.500   1.2358   0.06474   0.05619  -0.0506   0.0893   1.0000
   9.750   1.2568   0.07053   0.06215  -0.0500   0.0941   1.0000
  10.000   1.2309   0.07349   0.06599  -0.0452   0.0984   1.0000
  10.250   1.2210   0.07839   0.07126  -0.0428   0.1028   1.0000
  10.500   1.2134   0.08313   0.07632  -0.0409   0.1080   1.0000
  10.750   1.1804   0.08674   0.08021  -0.0379   0.1090   1.0000
  11.000   1.1487   0.09119   0.08487  -0.0369   0.1098   1.0000
  11.250   1.1168   0.09654   0.09038  -0.0376   0.1103   1.0000
  11.500   1.0845   0.10287   0.09683  -0.0400   0.1106   1.0000
  11.750   1.0510   0.11048   0.10452  -0.0441   0.1110   1.0000
  12.000   1.0178   0.11977   0.11383  -0.0501   0.1123   1.0000
  12.250   1.0084   0.12828   0.12236  -0.0539   0.1200   1.0000
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