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GOE 124 (MVA H.4) AIRFOIL (goe124-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 124 (MVA H.4) AIRFOIL (goe124-il)
Reynolds number: 100,000
Max Cl/Cd: 63.91 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe124-il-100000-n5.txt
Download as CSV file: xf-goe124-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 124 (MVA H.4) 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.2746   0.09608   0.09141  -0.0289   1.0000   0.0444
  -7.500  -0.2767   0.09427   0.08970  -0.0287   1.0000   0.0459
  -7.250  -0.2833   0.09309   0.08864  -0.0288   0.9985   0.0473
  -7.000  -0.2438   0.08944   0.08491  -0.0491   0.9790   0.0489
  -6.750  -0.2213   0.08420   0.07965  -0.0536   0.9696   0.0494
  -6.500  -0.2057   0.07979   0.07525  -0.0520   0.9625   0.0505
  -6.250  -0.1838   0.07611   0.07155  -0.0547   0.9517   0.0520
  -6.000  -0.1582   0.07252   0.06790  -0.0598   0.9402   0.0547
  -5.750  -0.0981   0.06867   0.06372  -0.0814   0.9251   0.0601
  -5.500  -0.0883   0.06413   0.05925  -0.0788   0.9164   0.0611
  -5.250  -0.0713   0.06110   0.05621  -0.0788   0.9047   0.0627
  -5.000  -0.0474   0.05814   0.05318  -0.0814   0.8936   0.0652
  -4.750   0.0119   0.05500   0.04949  -0.0959   0.8829   0.0728
  -4.500   0.0204   0.05116   0.04581  -0.0935   0.8722   0.0746
  -4.250   0.0394   0.04888   0.04353  -0.0934   0.8617   0.0783
  -4.000   0.0860   0.04581   0.03999  -0.1015   0.8527   0.0880
  -3.750   0.1048   0.04307   0.03729  -0.1013   0.8423   0.0901
  -3.500   0.1306   0.04091   0.03504  -0.1025   0.8328   0.0945
  -3.250   0.1655   0.03838   0.03222  -0.1060   0.8243   0.1050
  -3.000   0.1922   0.03648   0.03024  -0.1070   0.8145   0.1108
  -2.750   0.2241   0.03498   0.02847  -0.1091   0.8065   0.1301
  -2.500   0.2787   0.02923   0.02159  -0.1130   0.7985   0.0593
  -2.250   0.3075   0.02725   0.01945  -0.1138   0.7909   0.0573
  -2.000   0.3384   0.02557   0.01748  -0.1146   0.7813   0.0553
  -1.750   0.3693   0.02407   0.01561  -0.1151   0.7717   0.0537
  -1.500   0.3993   0.02282   0.01399  -0.1152   0.7612   0.0528
  -1.250   0.4280   0.02193   0.01285  -0.1152   0.7486   0.0544
  -1.000   0.4568   0.02113   0.01178  -0.1151   0.7369   0.0557
  -0.750   0.4857   0.02033   0.01072  -0.1149   0.7273   0.0555
  -0.500   0.5145   0.01965   0.00987  -0.1148   0.7179   0.0553
  -0.250   0.5430   0.01907   0.00913  -0.1147   0.7094   0.0553
   0.000   0.5712   0.01856   0.00851  -0.1144   0.7006   0.0556
   0.250   0.5991   0.01814   0.00802  -0.1143   0.6916   0.0562
   0.500   0.6266   0.01777   0.00757  -0.1139   0.6833   0.0570
   0.750   0.6542   0.01754   0.00731  -0.1137   0.6736   0.0593
   1.000   0.6817   0.01719   0.00696  -0.1135   0.6655   0.0628
   1.250   0.7091   0.01702   0.00677  -0.1133   0.6558   0.0651
   1.500   0.7368   0.01692   0.00659  -0.1130   0.6467   0.0676
   1.750   0.7645   0.01686   0.00644  -0.1128   0.6373   0.0708
   2.000   0.7922   0.01682   0.00639  -0.1126   0.6270   0.0764
   2.250   0.8200   0.01676   0.00635  -0.1124   0.6177   0.0948
   2.500   0.8399   0.01513   0.00647  -0.1108   0.6081   1.0000
   2.750   0.8673   0.01533   0.00652  -0.1105   0.5979   1.0000
   3.000   0.8944   0.01552   0.00658  -0.1102   0.5882   1.0000
   3.250   0.9213   0.01574   0.00674  -0.1099   0.5765   1.0000
   3.500   0.9482   0.01596   0.00691  -0.1097   0.5650   1.0000
   3.750   0.9749   0.01619   0.00709  -0.1094   0.5539   1.0000
   4.000   1.0015   0.01643   0.00728  -0.1091   0.5431   1.0000
   4.250   1.0279   0.01669   0.00754  -0.1088   0.5307   1.0000
   4.500   1.0540   0.01695   0.00780  -0.1085   0.5174   1.0000
   4.750   1.0798   0.01722   0.00804  -0.1081   0.5032   1.0000
   5.000   1.1054   0.01750   0.00830  -0.1076   0.4889   1.0000
   5.250   1.1308   0.01781   0.00861  -0.1072   0.4748   1.0000
   5.500   1.1560   0.01814   0.00893  -0.1067   0.4619   1.0000
   5.750   1.1811   0.01849   0.00927  -0.1062   0.4495   1.0000
   6.000   1.2059   0.01887   0.00967  -0.1058   0.4370   1.0000
   6.250   1.2305   0.01926   0.01013  -0.1053   0.4244   1.0000
   6.500   1.2548   0.01968   0.01059  -0.1048   0.4124   1.0000
   6.750   1.2786   0.02011   0.01106  -0.1042   0.4001   1.0000
   7.000   1.3019   0.02057   0.01158  -0.1035   0.3869   1.0000
   7.250   1.3245   0.02106   0.01210  -0.1028   0.3728   1.0000
   7.500   1.3469   0.02158   0.01266  -0.1020   0.3596   1.0000
   7.750   1.3687   0.02212   0.01330  -0.1011   0.3454   1.0000
   8.000   1.3895   0.02271   0.01399  -0.1002   0.3297   1.0000
   8.250   1.4093   0.02335   0.01471  -0.0991   0.3125   1.0000
   8.500   1.4283   0.02401   0.01550  -0.0980   0.2918   1.0000
   8.750   1.4452   0.02479   0.01635  -0.0965   0.2655   1.0000
   9.000   1.4588   0.02578   0.01731  -0.0948   0.2256   1.0000
   9.250   1.4655   0.02729   0.01853  -0.0924   0.1846   1.0000
   9.500   1.4700   0.02899   0.02003  -0.0898   0.1609   1.0000
   9.750   1.4738   0.03066   0.02163  -0.0872   0.1453   1.0000
  10.000   1.4757   0.03226   0.02325  -0.0842   0.1334   1.0000
  10.250   1.4774   0.03403   0.02504  -0.0817   0.1228   1.0000
  10.500   1.4788   0.03593   0.02699  -0.0795   0.1133   1.0000
  10.750   1.4836   0.03769   0.02891  -0.0778   0.1039   1.0000
  11.000   1.4849   0.03983   0.03114  -0.0762   0.0959   1.0000
  11.250   1.4882   0.04193   0.03338  -0.0749   0.0862   1.0000
  11.500   1.4906   0.04422   0.03580  -0.0739   0.0754   1.0000
  11.750   1.4894   0.04697   0.03861  -0.0729   0.0642   1.0000
  12.000   1.4852   0.05018   0.04185  -0.0722   0.0546   1.0000
  12.250   1.4787   0.05377   0.04548  -0.0716   0.0476   1.0000
  12.500   1.4712   0.05761   0.04937  -0.0712   0.0426   1.0000
  12.750   1.4636   0.06157   0.05342  -0.0709   0.0393   1.0000
  13.000   1.4565   0.06555   0.05756  -0.0709   0.0365   1.0000
  13.250   1.4478   0.06985   0.06195  -0.0710   0.0345   1.0000
  13.500   1.4390   0.07423   0.06642  -0.0713   0.0329   1.0000
  13.750   1.4329   0.07838   0.07073  -0.0716   0.0312   1.0000
  14.000   1.4264   0.08272   0.07521  -0.0722   0.0297   1.0000
  14.250   1.4192   0.08726   0.07987  -0.0730   0.0285   1.0000
  14.500   1.4109   0.09206   0.08477  -0.0740   0.0276   1.0000
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