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GOE 433 AIRFOIL (goe433-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 433 AIRFOIL (goe433-il)
Reynolds number: 50,000
Max Cl/Cd: 5.66 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe433-il-50000.txt
Download as CSV file: xf-goe433-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 433 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.2082   0.13172   0.12411  -0.0361   1.0000   0.2756
 -10.500  -0.2104   0.13065   0.12313  -0.0344   1.0000   0.2824
 -10.250  -0.2462   0.13383   0.12646  -0.0320   1.0000   0.2875
 -10.000  -0.2433   0.13058   0.12329  -0.0299   1.0000   0.2901
  -9.750  -0.2332   0.12775   0.12052  -0.0274   1.0000   0.2946
  -9.500  -0.2400   0.12708   0.11994  -0.0247   1.0000   0.2999
  -9.250  -0.2662   0.12852   0.12151  -0.0217   1.0000   0.3057
  -8.750  -0.2826   0.12604   0.11921  -0.0167   1.0000   0.3120
  -8.500  -0.2833   0.12486   0.11810  -0.0142   1.0000   0.3176
  -8.250  -0.3038   0.12547   0.11881  -0.0115   1.0000   0.3245
  -8.000  -0.3588   0.12926   0.12275  -0.0083   1.0000   0.3276
  -7.750  -0.3230   0.12317   0.11666  -0.0075   1.0000   0.3320
  -7.500  -0.3217   0.12170   0.11522  -0.0056   1.0000   0.3378
  -7.250  -0.3467   0.12231   0.11592  -0.0032   1.0000   0.3453
  -7.000  -0.3482   0.11998   0.11362  -0.0041   0.9970   0.3499
  -6.750  -0.3108   0.11617   0.10974  -0.0080   0.9903   0.3622
  -6.500  -0.3117   0.11416   0.10776  -0.0105   0.9828   0.3700
  -6.250  -0.2781   0.11071   0.10424  -0.0139   0.9761   0.3810
  -6.000  -0.2958   0.11003   0.10362  -0.0144   0.9680   0.3888
  -5.750  -0.2549   0.10626   0.09977  -0.0177   0.9609   0.4018
  -5.500  -0.2656   0.10502   0.09858  -0.0174   0.9529   0.4096
  -5.250  -0.2384   0.10236   0.09586  -0.0198   0.9456   0.4224
  -5.000  -0.2692   0.10228   0.09587  -0.0166   0.9371   0.4283
  -4.750  -0.3494   0.08386   0.07716  -0.0454   0.9331   0.2877
  -4.500  -0.3349   0.08266   0.07599  -0.0430   0.9255   0.2912
  -4.250  -0.3156   0.07633   0.06949  -0.0522   0.9184   0.2823
  -4.000  -0.2746   0.06807   0.06089  -0.0678   0.9118   0.2796
  -3.750  -0.2320   0.05996   0.05220  -0.0836   0.9042   0.2855
  -3.500  -0.1880   0.05811   0.05021  -0.0889   0.8960   0.2940
  -3.250  -0.1521   0.05525   0.04696  -0.0957   0.8875   0.3056
  -3.000  -0.1190   0.05490   0.04664  -0.0973   0.8791   0.3149
  -2.750  -0.0798   0.05330   0.04471  -0.1028   0.8705   0.3299
  -2.500  -0.0543   0.05358   0.04506  -0.1028   0.8616   0.3406
  -2.250  -0.0193   0.05343   0.04483  -0.1052   0.8532   0.3552
  -2.000   0.0082   0.05313   0.04439  -0.1072   0.8440   0.3704
  -1.750   0.0515   0.05336   0.04456  -0.1101   0.8356   0.3894
  -1.500   0.0567   0.05418   0.04549  -0.1074   0.8267   0.3986
  -1.250   0.0994   0.05450   0.04577  -0.1099   0.8183   0.4189
  -1.000   0.1110   0.05510   0.04635  -0.1092   0.8092   0.4323
  -0.750   0.1431   0.05553   0.04675  -0.1105   0.8008   0.4517
  -0.500   0.1675   0.05622   0.04742  -0.1110   0.7928   0.4707
  -0.250   0.1855   0.05691   0.04809  -0.1110   0.7844   0.4892
   0.000   0.2301   0.05731   0.04852  -0.1125   0.7768   0.5159
   0.250   0.2272   0.05854   0.04974  -0.1108   0.7692   0.5304
   0.500   0.2503   0.05927   0.05051  -0.1107   0.7620   0.5529
   0.750   0.2779   0.06001   0.05126  -0.1109   0.7546   0.5786
   1.000   0.2820   0.06127   0.05256  -0.1096   0.7482   0.5961
   1.250   0.3051   0.06219   0.05349  -0.1099   0.7422   0.6218
   1.500   0.3330   0.06304   0.05436  -0.1101   0.7356   0.6492
   1.750   0.3333   0.06464   0.05600  -0.1088   0.7308   0.6672
   2.000   0.3426   0.06604   0.05745  -0.1077   0.7269   0.6887
   2.250   0.3539   0.06747   0.05894  -0.1067   0.7244   0.7124
   2.500   0.3865   0.06828   0.05977  -0.1068   0.7170   0.7481
   2.750   0.3866   0.07006   0.06163  -0.1052   0.7158   0.7701
   3.000   0.3949   0.07185   0.06348  -0.1044   0.7165   0.7977
   3.250   0.3005   0.07847   0.07036  -0.1032   0.8249   0.7727
   3.500   0.3338   0.08078   0.07274  -0.1046   0.8180   0.8160
   3.750   0.3317   0.08130   0.07335  -0.1019   0.8127   0.8442
   4.000   0.3426   0.08182   0.07401  -0.1003   0.8026   0.8910
   4.250   0.3736   0.08443   0.07665  -0.1036   0.7959   1.0000
   4.500   0.3875   0.08553   0.07767  -0.1052   0.7826   1.0000
   4.750   0.4459   0.09075   0.08268  -0.1135   0.7769   1.0000
   5.000   0.4380   0.09064   0.08255  -0.1115   0.7639   1.0000
   5.250   0.4948   0.09590   0.08762  -0.1184   0.7571   1.0000
   5.500   0.4828   0.09569   0.08738  -0.1156   0.7439   1.0000
   5.750   0.5285   0.10040   0.09194  -0.1203   0.7371   1.0000
   6.000   0.5270   0.10086   0.09237  -0.1186   0.7223   1.0000
   6.250   0.5381   0.10321   0.09466  -0.1188   0.7122   1.0000
   6.500   0.5806   0.10704   0.09841  -0.1220   0.6999   1.0000
   6.750   0.5771   0.10796   0.09931  -0.1201   0.6849   1.0000
   7.000   0.5882   0.11030   0.10162  -0.1200   0.6719   1.0000
   7.250   0.6321   0.11464   0.10589  -0.1229   0.6602   1.0000
   7.500   0.6383   0.11597   0.10722  -0.1219   0.6434   1.0000
   7.750   0.6362   0.11776   0.10902  -0.1208   0.6292   1.0000
   8.000   0.6548   0.12098   0.11223  -0.1214   0.6176   1.0000
   8.500   0.6790   0.12586   0.11712  -0.1213   0.5878   1.0000
   8.750   0.6936   0.12940   0.12066  -0.1218   0.5785   1.0000
   9.000   0.7229   0.13259   0.12385  -0.1226   0.5637   1.0000
   9.250   0.7069   0.13461   0.12589  -0.1217   0.5539   1.0000
   9.500   0.7555   0.13963   0.13091  -0.1236   0.5429   1.0000
   9.750   0.7259   0.14064   0.13194  -0.1224   0.5352   1.0000
  10.000   0.7555   0.14441   0.13572  -0.1234   0.5259   1.0000
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