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GOE 57 AIRFOIL (goe57-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 57 AIRFOIL (goe57-il)
Reynolds number: 200,000
Max Cl/Cd: 70.23 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe57-il-200000-n5.txt
Download as CSV file: xf-goe57-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 57 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3050   0.09490   0.09157  -0.0250   1.0000   0.0236
  -7.500  -0.3099   0.09294   0.08967  -0.0236   1.0000   0.0235
  -7.250  -0.3209   0.09172   0.08855  -0.0215   1.0000   0.0242
  -7.000  -0.2871   0.08681   0.08361  -0.0375   0.9907   0.0252
  -6.750  -0.2626   0.08162   0.07839  -0.0438   0.9860   0.0252
  -6.500  -0.2538   0.07852   0.07532  -0.0403   0.9826   0.0269
  -6.250  -0.2247   0.07578   0.07255  -0.0463   0.9770   0.0326
  -6.000  -0.1750   0.07105   0.06769  -0.0631   0.9676   0.0342
  -5.750  -0.1425   0.06620   0.06274  -0.0702   0.9623   0.0343
  -5.250  -0.0963   0.05699   0.05346  -0.0773   0.9518   0.0360
  -5.000  -0.0757   0.05492   0.05138  -0.0781   0.9448   0.0386
  -4.750  -0.0394   0.05149   0.04784  -0.0841   0.9392   0.0420
  -4.250   0.0576   0.04460   0.04035  -0.0999   0.9254   0.0462
  -4.000   0.0911   0.04108   0.03664  -0.1034   0.9184   0.0462
  -3.750   0.1143   0.03682   0.03236  -0.1055   0.9105   0.0447
  -3.500   0.1442   0.03378   0.02917  -0.1079   0.9016   0.0428
  -3.250   0.1802   0.03099   0.02610  -0.1107   0.8935   0.0434
  -3.000   0.2123   0.02855   0.02340  -0.1123   0.8815   0.0437
  -2.750   0.2426   0.02617   0.02076  -0.1135   0.8678   0.0423
  -2.500   0.2730   0.02388   0.01817  -0.1143   0.8537   0.0412
  -2.250   0.3032   0.02173   0.01567  -0.1149   0.8409   0.0407
  -2.000   0.3328   0.01987   0.01348  -0.1152   0.8294   0.0408
  -1.750   0.3620   0.01831   0.01158  -0.1153   0.8175   0.0413
  -1.500   0.3904   0.01705   0.01001  -0.1152   0.8041   0.0420
  -1.250   0.4181   0.01609   0.00876  -0.1149   0.7885   0.0429
  -1.000   0.4454   0.01552   0.00796  -0.1145   0.7714   0.0448
  -0.750   0.4726   0.01491   0.00713  -0.1142   0.7543   0.0454
  -0.500   0.4998   0.01424   0.00626  -0.1138   0.7362   0.0454
  -0.250   0.5267   0.01370   0.00554  -0.1133   0.7162   0.0455
   0.000   0.5532   0.01327   0.00494  -0.1128   0.6928   0.0457
   0.250   0.5792   0.01296   0.00444  -0.1122   0.6663   0.0461
   0.500   0.6048   0.01257   0.00390  -0.1115   0.6397   0.0472
   0.750   0.6304   0.01234   0.00356  -0.1110   0.6153   0.0491
   1.000   0.6561   0.01228   0.00340  -0.1104   0.5901   0.0515
   1.250   0.6814   0.01229   0.00328  -0.1098   0.5596   0.0549
   1.500   0.7064   0.01238   0.00319  -0.1092   0.5247   0.0587
   1.750   0.7313   0.01247   0.00317  -0.1086   0.4897   0.0660
   2.000   0.7558   0.01265   0.00323  -0.1079   0.4552   0.0782
   2.250   0.7804   0.01284   0.00330  -0.1073   0.4237   0.0976
   2.500   0.8052   0.01290   0.00348  -0.1069   0.3956   0.1944
   3.000   0.8512   0.01212   0.00383  -0.1051   0.3447   1.0000
   3.250   0.8758   0.01249   0.00403  -0.1045   0.3185   1.0000
   3.500   0.9002   0.01288   0.00426  -0.1039   0.2918   1.0000
   3.750   0.9244   0.01329   0.00452  -0.1033   0.2656   1.0000
   4.000   0.9486   0.01371   0.00479  -0.1027   0.2435   1.0000
   4.250   0.9730   0.01410   0.00508  -0.1021   0.2284   1.0000
   4.500   0.9975   0.01446   0.00541  -0.1016   0.2185   1.0000
   4.750   1.0216   0.01488   0.00574  -0.1010   0.2071   1.0000
   5.000   1.0452   0.01532   0.00610  -0.1004   0.1951   1.0000
   5.250   1.0688   0.01576   0.00650  -0.0998   0.1875   1.0000
   5.750   1.1156   0.01665   0.00728  -0.0985   0.1629   1.0000
   6.000   1.1394   0.01704   0.00765  -0.0979   0.1509   1.0000
   6.250   1.1633   0.01742   0.00800  -0.0973   0.1336   1.0000
   6.500   1.1816   0.01846   0.00865  -0.0961   0.0690   1.0000
   6.750   1.1970   0.01994   0.00987  -0.0943   0.0214   1.0000
   7.000   1.2181   0.02068   0.01069  -0.0932   0.0177   1.0000
   7.250   1.2394   0.02138   0.01153  -0.0921   0.0162   1.0000
   7.500   1.2603   0.02209   0.01240  -0.0910   0.0156   1.0000
   7.750   1.2803   0.02287   0.01338  -0.0897   0.0146   1.0000
   8.000   1.2988   0.02377   0.01444  -0.0884   0.0134   1.0000
   8.250   1.3156   0.02479   0.01562  -0.0868   0.0126   1.0000
   8.500   1.3300   0.02594   0.01695  -0.0849   0.0121   1.0000
   8.750   1.3408   0.02728   0.01844  -0.0826   0.0117   1.0000
   9.000   1.3471   0.02882   0.02011  -0.0797   0.0113   1.0000
   9.250   1.3481   0.03051   0.02190  -0.0761   0.0111   1.0000
   9.500   1.3473   0.03245   0.02397  -0.0726   0.0109   1.0000
  10.000   1.3533   0.03608   0.02780  -0.0672   0.0103   1.0000
  10.250   1.3608   0.03758   0.02942  -0.0653   0.0099   1.0000
  10.500   1.3667   0.03930   0.03128  -0.0634   0.0095   1.0000
  10.750   1.3707   0.04131   0.03340  -0.0616   0.0092   1.0000
  11.000   1.3742   0.04349   0.03570  -0.0598   0.0090   1.0000
  11.250   1.3778   0.04577   0.03808  -0.0582   0.0088   1.0000
  11.500   1.3816   0.04811   0.04055  -0.0566   0.0087   1.0000
  11.750   1.3852   0.05056   0.04311  -0.0552   0.0085   1.0000
  12.000   1.3886   0.05310   0.04579  -0.0539   0.0084   1.0000
  12.250   1.3912   0.05579   0.04861  -0.0527   0.0083   1.0000
  12.500   1.3927   0.05864   0.05166  -0.0517   0.0082   1.0000
  12.750   1.3930   0.06169   0.05487  -0.0508   0.0081   1.0000
  13.000   1.3918   0.06498   0.05833  -0.0502   0.0081   1.0000
  13.250   1.3887   0.06852   0.06206  -0.0498   0.0080   1.0000
  13.500   1.3840   0.07237   0.06610  -0.0498   0.0080   1.0000
  13.750   1.3777   0.07651   0.07044  -0.0501   0.0080   1.0000
  14.000   1.3695   0.08100   0.07513  -0.0508   0.0080   1.0000
  14.250   1.3599   0.08584   0.08018  -0.0519   0.0080   1.0000
  14.500   1.3493   0.09103   0.08557  -0.0536   0.0080   1.0000
  14.750   1.3384   0.09646   0.09119  -0.0556   0.0079   1.0000
  15.000   1.3269   0.10227   0.09718  -0.0582   0.0079   1.0000
  15.250   1.3145   0.10854   0.10365  -0.0613   0.0079   1.0000
  15.500   1.3021   0.11509   0.11039  -0.0648   0.0079   1.0000
  15.750   1.2885   0.12221   0.11771  -0.0690   0.0080   1.0000
  16.000   1.2770   0.12913   0.12478  -0.0731   0.0079   1.0000
  16.250   1.2625   0.13724   0.13309  -0.0783   0.0080   1.0000
  16.500   1.2482   0.14576   0.14180  -0.0840   0.0081   1.0000
  16.750   1.2338   0.15474   0.15095  -0.0900   0.0082   1.0000
  17.000   1.2182   0.16471   0.16110  -0.0968   0.0084   1.0000
  17.250   1.2033   0.17508   0.17162  -0.1038   0.0085   1.0000
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