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GOE 124 (MVA H.4) AIRFOIL (goe124-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 124 (MVA H.4) AIRFOIL (goe124-il)
Reynolds number: 1,000,000
Max Cl/Cd: 126.4 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe124-il-1000000-n5.txt
Download as CSV file: xf-goe124-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3322   0.09570   0.09364  -0.0209   0.8390   0.0095
  -8.500  -0.3333   0.09020   0.08809  -0.0239   0.8247   0.0105
  -8.250  -0.3232   0.08793   0.08577  -0.0254   0.8103   0.0107
  -8.000  -0.3135   0.08552   0.08331  -0.0271   0.7963   0.0108
  -7.750  -0.3029   0.08299   0.08074  -0.0293   0.7833   0.0110
  -7.500  -0.2890   0.07998   0.07769  -0.0327   0.7716   0.0113
  -7.250  -0.2737   0.07662   0.07426  -0.0368   0.7603   0.0116
  -7.000  -0.2574   0.06879   0.06637  -0.0471   0.7504   0.0131
  -6.750  -0.2365   0.06627   0.06380  -0.0508   0.7402   0.0133
  -6.500  -0.2143   0.06367   0.06114  -0.0546   0.7302   0.0135
  -6.250  -0.1907   0.06082   0.05824  -0.0587   0.7210   0.0137
  -6.000  -0.1653   0.05761   0.05495  -0.0634   0.7112   0.0141
  -5.750  -0.1374   0.05383   0.05108  -0.0689   0.7009   0.0147
  -5.500  -0.0965   0.04498   0.04202  -0.0812   0.6930   0.0163
  -5.000  -0.0396   0.04049   0.03733  -0.0870   0.6727   0.0168
  -4.750  -0.0092   0.03794   0.03465  -0.0901   0.6640   0.0171
  -4.500   0.0224   0.03518   0.03177  -0.0932   0.6553   0.0177
  -4.250   0.0580   0.03104   0.02740  -0.0973   0.6475   0.0185
  -4.000   0.1038   0.02145   0.01712  -0.1039   0.6405   0.0201
  -3.750   0.1337   0.01998   0.01546  -0.1051   0.6321   0.0203
  -3.500   0.1634   0.01874   0.01404  -0.1060   0.6228   0.0206
  -3.250   0.1932   0.01767   0.01281  -0.1067   0.6142   0.0209
  -3.000   0.2235   0.01640   0.01133  -0.1075   0.6062   0.0211
  -2.750   0.2541   0.01512   0.00983  -0.1083   0.5997   0.0214
  -2.500   0.2849   0.01384   0.00831  -0.1090   0.5926   0.0217
  -2.250   0.3152   0.01283   0.00709  -0.1096   0.5868   0.0220
  -2.000   0.3453   0.01199   0.00608  -0.1100   0.5805   0.0224
  -1.750   0.3752   0.01120   0.00511  -0.1105   0.5741   0.0227
  -1.500   0.4048   0.01065   0.00445  -0.1108   0.5678   0.0232
  -1.250   0.4341   0.01029   0.00399  -0.1110   0.5602   0.0236
  -1.000   0.4633   0.01002   0.00365  -0.1113   0.5526   0.0239
  -0.750   0.4923   0.00983   0.00339  -0.1115   0.5442   0.0241
  -0.500   0.5213   0.00966   0.00317  -0.1117   0.5368   0.0243
  -0.250   0.5503   0.00948   0.00295  -0.1119   0.5285   0.0244
   0.000   0.5798   0.00908   0.00250  -0.1122   0.5205   0.0248
   0.250   0.6089   0.00891   0.00228  -0.1125   0.5114   0.0252
   0.500   0.6379   0.00881   0.00216  -0.1127   0.5012   0.0257
   0.750   0.6666   0.00879   0.00210  -0.1129   0.4863   0.0263
   1.000   0.6952   0.00880   0.00204  -0.1131   0.4690   0.0268
   1.250   0.7239   0.00881   0.00199  -0.1133   0.4531   0.0273
   1.500   0.7524   0.00885   0.00197  -0.1134   0.4368   0.0279
   1.750   0.7808   0.00893   0.00197  -0.1136   0.4193   0.0287
   2.000   0.8089   0.00906   0.00201  -0.1137   0.3956   0.0294
   2.250   0.8368   0.00923   0.00207  -0.1138   0.3743   0.0299
   2.500   0.8650   0.00933   0.00213  -0.1139   0.3615   0.0304
   2.750   0.8933   0.00940   0.00218  -0.1140   0.3519   0.0310
   3.000   0.9214   0.00949   0.00224  -0.1141   0.3432   0.0331
   3.250   0.9497   0.00957   0.00232  -0.1142   0.3360   0.0359
   3.750   1.0066   0.00959   0.00260  -0.1147   0.3208   0.2223
   4.250   1.0576   0.00853   0.00302  -0.1143   0.3073   1.0000
   4.500   1.0853   0.00871   0.00316  -0.1143   0.3008   1.0000
   4.750   1.1130   0.00887   0.00330  -0.1143   0.2941   1.0000
   5.000   1.1405   0.00904   0.00345  -0.1144   0.2867   1.0000
   5.250   1.1679   0.00924   0.00362  -0.1144   0.2779   1.0000
   5.500   1.1949   0.00947   0.00380  -0.1143   0.2662   1.0000
   5.750   1.2217   0.00974   0.00400  -0.1143   0.2507   1.0000
   6.000   1.2431   0.01078   0.00459  -0.1137   0.1712   1.0000
   6.250   1.2654   0.01165   0.00519  -0.1131   0.1262   1.0000
   6.500   1.2908   0.01203   0.00552  -0.1129   0.1152   1.0000
   6.750   1.3167   0.01233   0.00581  -0.1127   0.1086   1.0000
   7.000   1.3420   0.01269   0.00613  -0.1124   0.1010   1.0000
   7.250   1.3675   0.01299   0.00643  -0.1122   0.0951   1.0000
   7.500   1.3926   0.01334   0.00675  -0.1119   0.0881   1.0000
   7.750   1.4171   0.01373   0.00711  -0.1116   0.0788   1.0000
   8.000   1.4408   0.01420   0.00751  -0.1111   0.0673   1.0000
   8.250   1.4637   0.01473   0.00797  -0.1106   0.0552   1.0000
   8.500   1.4850   0.01542   0.00856  -0.1098   0.0410   1.0000
   8.750   1.5026   0.01645   0.00944  -0.1085   0.0193   1.0000
   9.000   1.5235   0.01707   0.01006  -0.1077   0.0148   1.0000
   9.250   1.5444   0.01765   0.01065  -0.1068   0.0127   1.0000
   9.500   1.5658   0.01814   0.01118  -0.1060   0.0118   1.0000
   9.750   1.5862   0.01870   0.01177  -0.1051   0.0109   1.0000
  10.000   1.6052   0.01933   0.01243  -0.1039   0.0100   1.0000
  10.250   1.6235   0.01997   0.01312  -0.1027   0.0092   1.0000
  10.500   1.6417   0.02056   0.01375  -0.1015   0.0088   1.0000
  10.750   1.6583   0.02120   0.01445  -0.1000   0.0082   1.0000
  11.000   1.6726   0.02191   0.01520  -0.0982   0.0078   1.0000
  11.250   1.6828   0.02271   0.01604  -0.0957   0.0074   1.0000
  11.500   1.6911   0.02367   0.01707  -0.0932   0.0070   1.0000
  11.750   1.6999   0.02471   0.01817  -0.0909   0.0068   1.0000
  12.000   1.7096   0.02577   0.01930  -0.0891   0.0066   1.0000
  12.250   1.7187   0.02695   0.02057  -0.0873   0.0064   1.0000
  12.500   1.7272   0.02827   0.02196  -0.0857   0.0062   1.0000
  12.750   1.7348   0.02973   0.02349  -0.0842   0.0060   1.0000
  13.000   1.7417   0.03133   0.02517  -0.0829   0.0058   1.0000
  13.250   1.7478   0.03307   0.02698  -0.0817   0.0056   1.0000
  13.500   1.7527   0.03501   0.02899  -0.0806   0.0054   1.0000
  13.750   1.7564   0.03715   0.03121  -0.0796   0.0052   1.0000
  14.000   1.7578   0.03959   0.03374  -0.0786   0.0050   1.0000
  14.250   1.7563   0.04244   0.03668  -0.0778   0.0049   1.0000
  14.500   1.7584   0.04496   0.03930  -0.0772   0.0048   1.0000
  14.750   1.7587   0.04772   0.04216  -0.0767   0.0047   1.0000
  15.000   1.7576   0.05069   0.04523  -0.0763   0.0047   1.0000
  15.250   1.7552   0.05388   0.04852  -0.0760   0.0046   1.0000
  15.500   1.7517   0.05728   0.05203  -0.0758   0.0045   1.0000
  15.750   1.7473   0.06090   0.05575  -0.0758   0.0044   1.0000
  16.000   1.7422   0.06471   0.05967  -0.0760   0.0044   1.0000
  16.250   1.7364   0.06873   0.06379  -0.0763   0.0043   1.0000
  16.500   1.7292   0.07300   0.06817  -0.0768   0.0042   1.0000
  16.750   1.7218   0.07741   0.07268  -0.0774   0.0042   1.0000
  17.000   1.7134   0.08208   0.07747  -0.0783   0.0041   1.0000
  17.250   1.7046   0.08688   0.08238  -0.0793   0.0041   1.0000
  17.500   1.6944   0.09194   0.08755  -0.0804   0.0040   1.0000
  17.750   1.6840   0.09717   0.09288  -0.0818   0.0040   1.0000
  18.000   1.6730   0.10257   0.09839  -0.0833   0.0039   1.0000
  18.250   1.6616   0.10809   0.10403  -0.0850   0.0039   1.0000
  18.500   1.6495   0.11378   0.10983  -0.0868   0.0038   1.0000
  18.750   1.6376   0.11954   0.11569  -0.0889   0.0038   1.0000
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