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GOE 225 (MVA H.35) AIRFOIL (goe225-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 225 (MVA H.35) AIRFOIL (goe225-il)
Reynolds number: 100,000
Max Cl/Cd: 63.52 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe225-il-100000-n5.txt
Download as CSV file: xf-goe225-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 225 (MVA H.35) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.0648   0.11300   0.10756  -0.0928   0.9455   0.0768
  -9.500  -0.0578   0.11014   0.10469  -0.0968   0.9430   0.0771
  -9.250  -0.0565   0.10787   0.10245  -0.0971   0.9372   0.0771
  -8.750  -0.0383   0.09787   0.09238  -0.1005   0.9305   0.0600
  -8.500  -0.0190   0.09475   0.08923  -0.1022   0.9281   0.0588
  -8.250  -0.0143   0.09217   0.08666  -0.1031   0.9225   0.0587
  -8.000  -0.0092   0.08962   0.08411  -0.1038   0.9162   0.0584
  -7.750   0.0030   0.08642   0.08090  -0.1061   0.9121   0.0577
  -7.500   0.0065   0.08382   0.07830  -0.1066   0.9059   0.0566
  -7.250   0.0063   0.08118   0.07568  -0.1069   0.8980   0.0557
  -7.000   0.0186   0.07669   0.07116  -0.1117   0.8935   0.0546
  -6.750   0.0132   0.07333   0.06781  -0.1129   0.8835   0.0538
  -6.500   0.0256   0.06831   0.06276  -0.1190   0.8784   0.0534
  -6.250   0.0493   0.06509   0.05949  -0.1237   0.8756   0.0544
  -6.000   0.0495   0.06262   0.05705  -0.1247   0.8665   0.0549
  -5.750   0.1548   0.03376   0.02670  -0.1838   0.8632   0.0556
  -5.500   0.2033   0.03053   0.02290  -0.1911   0.8611   0.0573
  -5.250   0.2481   0.02831   0.02019  -0.1960   0.8591   0.0601
  -5.000   0.2761   0.02783   0.01969  -0.1966   0.8544   0.0620
  -4.750   0.3039   0.02713   0.01885  -0.1973   0.8485   0.0643
  -4.500   0.3408   0.02594   0.01738  -0.1994   0.8451   0.0674
  -4.250   0.3777   0.02515   0.01654  -0.2013   0.8422   0.0706
  -4.000   0.4144   0.02436   0.01559  -0.2030   0.8392   0.0763
  -3.750   0.4356   0.02427   0.01552  -0.2021   0.8310   0.0818
  -3.500   0.4701   0.02366   0.01482  -0.2034   0.8268   0.0920
  -3.250   0.5074   0.02297   0.01401  -0.2051   0.8236   0.1042
  -3.000   0.5324   0.02282   0.01377  -0.2047   0.8161   0.1148
  -2.750   0.5630   0.02242   0.01339  -0.2053   0.8103   0.1265
  -2.500   0.5984   0.02193   0.01287  -0.2066   0.8063   0.1448
  -2.250   0.6234   0.02181   0.01280  -0.2062   0.7984   0.1589
  -2.000   0.6536   0.02148   0.01248  -0.2064   0.7918   0.1706
  -1.750   0.6890   0.02097   0.01196  -0.2075   0.7875   0.1832
  -1.500   0.7110   0.02100   0.01203  -0.2064   0.7770   0.1964
  -1.250   0.7443   0.02061   0.01170  -0.2071   0.7713   0.2213
  -1.000   0.7677   0.02064   0.01179  -0.2061   0.7606   0.2496
  -0.750   0.7998   0.02036   0.01145  -0.2065   0.7540   0.2812
  -0.500   0.8220   0.02045   0.01158  -0.2053   0.7419   0.3035
  -0.250   0.8496   0.02035   0.01147  -0.2050   0.7324   0.3257
   0.000   0.8769   0.02024   0.01136  -0.2046   0.7218   0.3449
   0.250   0.9013   0.02028   0.01140  -0.2038   0.7089   0.3607
   0.500   0.9282   0.02023   0.01135  -0.2033   0.6971   0.3784
   0.750   0.9581   0.02008   0.01116  -0.2033   0.6869   0.3986
   1.000   0.9858   0.02003   0.01108  -0.2029   0.6748   0.4163
   1.250   1.0137   0.02000   0.01102  -0.2026   0.6630   0.4348
   1.500   1.0433   0.01993   0.01088  -0.2025   0.6525   0.4534
   1.750   1.0727   0.01990   0.01078  -0.2025   0.6419   0.4705
   2.000   1.1003   0.01997   0.01079  -0.2022   0.6310   0.4865
   2.250   1.1298   0.02000   0.01072  -0.2022   0.6216   0.5025
   2.500   1.1567   0.02015   0.01082  -0.2019   0.6117   0.5186
   2.750   1.1847   0.02028   0.01089  -0.2018   0.6030   0.5356
   3.000   1.2112   0.02047   0.01105  -0.2015   0.5940   0.5540
   3.250   1.2385   0.02065   0.01120  -0.2013   0.5862   0.5742
   3.500   1.2641   0.02089   0.01145  -0.2008   0.5777   0.5957
   3.750   1.2917   0.02107   0.01161  -0.2007   0.5704   0.6195
   4.000   1.3154   0.02133   0.01196  -0.1999   0.5619   0.6480
   4.250   1.3421   0.02141   0.01209  -0.1996   0.5541   0.6955
   4.500   1.3586   0.02145   0.01241  -0.1974   0.5446   1.0000
   4.750   1.3859   0.02182   0.01261  -0.1972   0.5361   1.0000
   5.000   1.4071   0.02229   0.01310  -0.1961   0.5266   1.0000
   5.250   1.4337   0.02268   0.01338  -0.1959   0.5191   1.0000
   5.500   1.4543   0.02317   0.01393  -0.1947   0.5108   1.0000
   5.750   1.4783   0.02360   0.01431  -0.1941   0.5033   1.0000
   6.000   1.5000   0.02409   0.01483  -0.1931   0.4957   1.0000
   6.250   1.5209   0.02457   0.01533  -0.1919   0.4878   1.0000
   6.500   1.5435   0.02503   0.01577  -0.1911   0.4808   1.0000
   6.750   1.5613   0.02558   0.01641  -0.1895   0.4726   1.0000
   7.000   1.5839   0.02602   0.01683  -0.1886   0.4657   1.0000
   7.250   1.5987   0.02663   0.01757  -0.1865   0.4573   1.0000
   7.500   1.6175   0.02714   0.01809  -0.1850   0.4498   1.0000
   7.750   1.6314   0.02776   0.01883  -0.1828   0.4414   1.0000
   8.000   1.6455   0.02833   0.01944  -0.1806   0.4333   1.0000
   8.250   1.6568   0.02901   0.02021  -0.1779   0.4249   1.0000
   8.500   1.6692   0.02968   0.02094  -0.1755   0.4167   1.0000
   8.750   1.6802   0.03047   0.02184  -0.1730   0.4081   1.0000
   9.000   1.6910   0.03124   0.02266  -0.1705   0.3992   1.0000
   9.250   1.6984   0.03221   0.02374  -0.1677   0.3889   1.0000
   9.500   1.7066   0.03315   0.02470  -0.1651   0.3786   1.0000
   9.750   1.7119   0.03429   0.02590  -0.1622   0.3670   1.0000
  10.000   1.7166   0.03556   0.02725  -0.1594   0.3550   1.0000
  10.250   1.7216   0.03686   0.02860  -0.1567   0.3436   1.0000
  10.500   1.7265   0.03824   0.02997  -0.1541   0.3327   1.0000
  10.750   1.7306   0.03979   0.03162  -0.1517   0.3216   1.0000
  11.000   1.7350   0.04135   0.03323  -0.1493   0.3117   1.0000
  11.250   1.7389   0.04301   0.03493  -0.1470   0.3021   1.0000
  11.500   1.7417   0.04482   0.03683  -0.1447   0.2923   1.0000
  11.750   1.7434   0.04672   0.03873  -0.1424   0.2829   1.0000
  12.000   1.7441   0.04882   0.04091  -0.1402   0.2731   1.0000
  12.250   1.7449   0.05093   0.04308  -0.1381   0.2646   1.0000
  12.500   1.7453   0.05316   0.04538  -0.1361   0.2564   1.0000
  12.750   1.7462   0.05542   0.04772  -0.1343   0.2491   1.0000
  13.000   1.7459   0.05790   0.05030  -0.1325   0.2416   1.0000
  13.250   1.7457   0.06039   0.05285  -0.1309   0.2348   1.0000
  13.500   1.7435   0.06325   0.05585  -0.1294   0.2272   1.0000
  13.750   1.7397   0.06629   0.05893  -0.1280   0.2194   1.0000
  14.000   1.7335   0.06984   0.06261  -0.1269   0.2105   1.0000
  14.250   1.7274   0.07343   0.06627  -0.1260   0.2025   1.0000
  14.500   1.7202   0.07734   0.07031  -0.1253   0.1940   1.0000
  14.750   1.7128   0.08140   0.07448  -0.1248   0.1860   1.0000
  15.000   1.7028   0.08594   0.07910  -0.1246   0.1769   1.0000
  15.250   1.6920   0.09079   0.08408  -0.1248   0.1668   1.0000
  15.500   1.6809   0.09572   0.08911  -0.1251   0.1572   1.0000
  15.750   1.6682   0.10100   0.09445  -0.1256   0.1470   1.0000
  16.000   1.6557   0.10640   0.09997  -0.1265   0.1349   1.0000
  16.250   1.6413   0.11216   0.10578  -0.1276   0.1211   1.0000
  16.500   1.6256   0.11820   0.11184  -0.1290   0.1058   1.0000
  16.750   1.6084   0.12458   0.11817  -0.1308   0.0913   1.0000
  17.000   1.5912   0.13108   0.12463  -0.1329   0.0810   1.0000
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