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GOE 115 (MVA MK.2) AIRFOIL (goe115-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 115 (MVA MK.2) AIRFOIL (goe115-il)
Reynolds number: 50,000
Max Cl/Cd: 32.21 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe115-il-50000.txt
Download as CSV file: xf-goe115-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 115 (MVA MK.2) 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3796   0.12332   0.11632  -0.0250   1.0000   0.2185
  -9.750  -0.3594   0.11787   0.11084  -0.0243   1.0000   0.2256
  -9.500  -0.3749   0.11815   0.11125  -0.0259   1.0000   0.2314
  -9.250  -0.3524   0.11187   0.10492  -0.0251   1.0000   0.2370
  -9.000  -0.3572   0.11046   0.10360  -0.0258   1.0000   0.2443
  -8.750  -0.3470   0.10629   0.09946  -0.0256   1.0000   0.2498
  -8.500  -0.3521   0.10481   0.09808  -0.0259   1.0000   0.2586
  -8.250  -0.3427   0.10074   0.09406  -0.0256   1.0000   0.2636
  -8.000  -0.3415   0.09832   0.09171  -0.0253   1.0000   0.2713
  -7.750  -0.3524   0.09669   0.09023  -0.0252   1.0000   0.2754
  -7.500  -0.3384   0.09244   0.08599  -0.0244   1.0000   0.2801
  -7.250  -0.3506   0.09130   0.08501  -0.0234   1.0000   0.2870
  -7.000  -0.3629   0.08952   0.08341  -0.0219   1.0000   0.2899
  -6.750  -0.3562   0.08600   0.07994  -0.0206   1.0000   0.2928
  -6.500  -0.3622   0.08387   0.07794  -0.0186   1.0000   0.2961
  -6.250  -0.3970   0.08449   0.07884  -0.0176   1.0000   0.3032
  -6.000  -0.4006   0.08159   0.07602  -0.0157   1.0000   0.3039
  -5.750  -0.4089   0.07934   0.07387  -0.0140   1.0000   0.3043
  -5.500  -0.4247   0.05913   0.05320  -0.0453   1.0000   0.1472
  -5.000  -0.4032   0.04668   0.04007  -0.0517   1.0000   0.1282
  -4.750  -0.3810   0.03911   0.03124  -0.0567   1.0000   0.1199
  -4.500  -0.3614   0.03601   0.02756  -0.0572   1.0000   0.1203
  -4.250  -0.3429   0.03396   0.02537  -0.0568   1.0000   0.1239
  -4.000  -0.3217   0.03191   0.02290  -0.0566   1.0000   0.1255
  -3.750  -0.3002   0.03020   0.02078  -0.0562   1.0000   0.1273
  -3.500  -0.2791   0.02889   0.01912  -0.0556   1.0000   0.1307
  -3.250  -0.2590   0.02794   0.01801  -0.0549   1.0000   0.1377
  -3.000  -0.2380   0.02721   0.01702  -0.0543   1.0000   0.1482
  -2.750  -0.2182   0.02649   0.01633  -0.0535   1.0000   0.1596
  -2.500  -0.1955   0.02592   0.01585  -0.0532   1.0000   0.1809
  -2.250  -0.1741   0.02579   0.01622  -0.0526   1.0000   0.2537
  -2.000  -0.1431   0.02690   0.01737  -0.0537   0.9917   0.3881
  -1.750  -0.1117   0.02765   0.01816  -0.0547   0.9836   0.4500
  -1.500  -0.0844   0.02807   0.01857  -0.0552   0.9759   0.4940
  -1.250  -0.0486   0.02849   0.01883  -0.0574   0.9690   0.5249
  -1.000  -0.0205   0.02869   0.01891  -0.0584   0.9615   0.5532
  -0.750   0.0143   0.02904   0.01922  -0.0603   0.9551   0.5932
  -0.500   0.0368   0.02910   0.01939  -0.0601   0.9485   0.6360
  -0.250   0.0719   0.02926   0.01964  -0.0621   0.9425   0.6785
   0.000   0.0980   0.02923   0.01982  -0.0627   0.9364   0.7247
   0.250   0.1411   0.02889   0.01997  -0.0669   0.9300   1.0000
   0.500   0.1786   0.02979   0.02037  -0.0709   0.9240   1.0000
   0.750   0.2075   0.03063   0.02083  -0.0727   0.9177   1.0000
   1.000   0.2425   0.03163   0.02153  -0.0753   0.9121   1.0000
   1.250   0.2601   0.03244   0.02215  -0.0749   0.9060   1.0000
   1.500   0.2923   0.03344   0.02297  -0.0768   0.8998   1.0000
   1.750   0.3111   0.03435   0.02376  -0.0766   0.8936   1.0000
   2.000   0.3402   0.03535   0.02464  -0.0779   0.8864   1.0000
   2.250   0.3615   0.03631   0.02553  -0.0780   0.8784   1.0000
   2.500   0.3987   0.03736   0.02652  -0.0804   0.8691   1.0000
   2.750   0.4177   0.03828   0.02742  -0.0800   0.8590   1.0000
   3.000   0.4416   0.03931   0.02843  -0.0804   0.8491   1.0000
   3.250   0.4751   0.04038   0.02952  -0.0821   0.8393   1.0000
   3.500   0.4967   0.04144   0.03060  -0.0822   0.8291   1.0000
   3.750   0.5160   0.04258   0.03182  -0.0819   0.8187   1.0000
   4.000   0.5429   0.04374   0.03303  -0.0826   0.8079   1.0000
   4.250   0.5772   0.04485   0.03425  -0.0842   0.7968   1.0000
   4.500   0.5954   0.04609   0.03558  -0.0838   0.7850   1.0000
   4.750   0.6135   0.04740   0.03703  -0.0834   0.7726   1.0000
   5.000   0.6336   0.04876   0.03851  -0.0832   0.7601   1.0000
   5.250   0.6553   0.05013   0.04002  -0.0832   0.7470   1.0000
   5.500   0.6770   0.05156   0.04161  -0.0832   0.7340   1.0000
   5.750   0.6988   0.05303   0.04326  -0.0832   0.7208   1.0000
   6.000   0.7213   0.05455   0.04501  -0.0833   0.7081   1.0000
   6.250   0.7455   0.05606   0.04674  -0.0834   0.6954   1.0000
   6.500   0.7704   0.05757   0.04851  -0.0836   0.6831   1.0000
   6.750   0.7776   0.05967   0.05078  -0.0825   0.6703   1.0000
   7.000   0.9647   0.02995   0.01939  -0.0562   0.1638   1.0000
   7.250   0.9580   0.03245   0.02154  -0.0522   0.1400   1.0000
   7.500   0.9554   0.03474   0.02369  -0.0489   0.1255   1.0000
   7.750   0.9577   0.03688   0.02578  -0.0460   0.1163   1.0000
   8.000   0.9678   0.03880   0.02764  -0.0435   0.1092   1.0000
   8.250   1.0084   0.04025   0.02914  -0.0425   0.1004   1.0000
   8.500   1.1053   0.04373   0.03266  -0.0480   0.0908   1.0000
   8.750   1.1495   0.04727   0.03655  -0.0489   0.0906   1.0000
   9.000   1.1771   0.05081   0.04051  -0.0481   0.0905   1.0000
   9.250   1.1949   0.05429   0.04444  -0.0466   0.0900   1.0000
   9.500   1.2077   0.05800   0.04859  -0.0447   0.0903   1.0000
   9.750   1.2200   0.06229   0.05325  -0.0430   0.0921   1.0000
  10.000   1.2388   0.06749   0.05870  -0.0423   0.0952   1.0000
  10.250   1.2142   0.06976   0.06179  -0.0373   0.0985   1.0000
  10.500   1.1977   0.07387   0.06635  -0.0343   0.1017   1.0000
  10.750   1.1883   0.07855   0.07128  -0.0324   0.1048   1.0000
  11.000   1.1830   0.08316   0.07612  -0.0307   0.1089   1.0000
  11.250   1.1475   0.08658   0.07979  -0.0284   0.1096   1.0000
  11.500   1.1120   0.09124   0.08463  -0.0284   0.1103   1.0000
  11.750   1.0753   0.09714   0.09067  -0.0304   0.1107   1.0000
  12.000   1.0348   0.10485   0.09847  -0.0348   0.1112   1.0000
  12.250   0.9860   0.11652   0.11016  -0.0433   0.1156   1.0000
  12.500   0.9999   0.12182   0.11551  -0.0429   0.1212   1.0000
  12.750   0.9384   0.14270   0.13619  -0.0599   0.1487   1.0000
  13.000   0.7607   0.14306   0.13702  -0.0548   0.1450   1.0000
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