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GOE 57 AIRFOIL (goe57-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 57 AIRFOIL (goe57-il)
Reynolds number: 500,000
Max Cl/Cd: 86.46 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe57-il-500000-n5.txt
Download as CSV file: xf-goe57-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3313   0.10121   0.09897  -0.0249   1.0000   0.0089
  -8.750  -0.3308   0.09751   0.09530  -0.0258   1.0000   0.0092
  -8.500  -0.3333   0.09381   0.09163  -0.0264   1.0000   0.0097
  -8.250  -0.3298   0.09211   0.08998  -0.0260   1.0000   0.0100
  -8.000  -0.3285   0.09065   0.08855  -0.0250   1.0000   0.0103
  -7.750  -0.3093   0.08728   0.08517  -0.0296   0.9950   0.0108
  -7.500  -0.2895   0.08298   0.08087  -0.0355   0.9870   0.0113
  -7.250  -0.2689   0.07804   0.07591  -0.0424   0.9775   0.0121
  -7.000  -0.2458   0.07070   0.06854  -0.0530   0.9653   0.0135
  -6.750  -0.2194   0.06859   0.06640  -0.0571   0.9542   0.0140
  -6.500  -0.1913   0.06556   0.06333  -0.0625   0.9423   0.0148
  -6.250  -0.1623   0.06140   0.05910  -0.0694   0.9297   0.0158
  -6.000  -0.1239   0.05246   0.04998  -0.0834   0.9161   0.0186
  -5.750  -0.0992   0.05081   0.04827  -0.0856   0.9062   0.0191
  -5.500  -0.0740   0.04891   0.04629  -0.0880   0.8965   0.0197
  -5.250  -0.0466   0.04640   0.04368  -0.0913   0.8868   0.0205
  -5.000  -0.0171   0.04349   0.04064  -0.0951   0.8769   0.0221
  -4.750   0.0171   0.03916   0.03611  -0.1005   0.8670   0.0234
  -4.500   0.0549   0.03428   0.03096  -0.1056   0.8584   0.0250
  -4.250   0.0840   0.03075   0.02720  -0.1085   0.8487   0.0263
  -4.000   0.1106   0.02909   0.02538  -0.1095   0.8342   0.0268
  -3.750   0.1377   0.02734   0.02344  -0.1104   0.8167   0.0273
  -3.500   0.1660   0.02524   0.02110  -0.1114   0.7997   0.0277
  -3.250   0.1954   0.02278   0.01838  -0.1124   0.7864   0.0280
  -3.000   0.2239   0.02100   0.01637  -0.1131   0.7740   0.0286
  -2.750   0.2538   0.01813   0.01312  -0.1138   0.7607   0.0287
  -2.500   0.2831   0.01522   0.00974  -0.1143   0.7461   0.0291
  -2.250   0.3109   0.01370   0.00786  -0.1143   0.7271   0.0300
  -2.000   0.3377   0.01282   0.00665  -0.1141   0.6992   0.0309
  -1.750   0.3639   0.01225   0.00578  -0.1136   0.6672   0.0317
  -1.500   0.3903   0.01182   0.00509  -0.1133   0.6410   0.0322
  -1.250   0.4168   0.01147   0.00453  -0.1130   0.6169   0.0326
  -1.000   0.4434   0.01116   0.00404  -0.1127   0.5957   0.0329
  -0.750   0.4702   0.01092   0.00365  -0.1124   0.5742   0.0332
  -0.500   0.4967   0.01084   0.00343  -0.1121   0.5488   0.0337
  -0.250   0.5228   0.01081   0.00323  -0.1117   0.5153   0.0341
   0.000   0.5480   0.01081   0.00298  -0.1112   0.4683   0.0342
   0.250   0.5736   0.01081   0.00277  -0.1108   0.4286   0.0343
   0.500   0.5993   0.01085   0.00262  -0.1104   0.3942   0.0345
   0.750   0.6253   0.01078   0.00238  -0.1101   0.3630   0.0353
   1.000   0.6513   0.01084   0.00228  -0.1098   0.3313   0.0369
   1.250   0.6772   0.01099   0.00230  -0.1095   0.3011   0.0391
   1.500   0.7032   0.01117   0.00236  -0.1091   0.2717   0.0419
   1.750   0.7287   0.01143   0.00245  -0.1087   0.2349   0.0449
   2.000   0.7540   0.01171   0.00257  -0.1084   0.2022   0.0491
   2.250   0.7802   0.01187   0.00269  -0.1081   0.1893   0.0564
   2.500   0.8068   0.01199   0.00280  -0.1078   0.1837   0.0665
   2.750   0.8333   0.01208   0.00296  -0.1076   0.1797   0.0972
   3.000   0.8599   0.01208   0.00317  -0.1075   0.1764   0.1996
   3.500   0.9088   0.01098   0.00359  -0.1064   0.1720   1.0000
   3.750   0.9350   0.01118   0.00376  -0.1061   0.1673   1.0000
   4.000   0.9606   0.01146   0.00396  -0.1058   0.1612   1.0000
   4.250   0.9866   0.01168   0.00417  -0.1054   0.1577   1.0000
   4.500   1.0129   0.01185   0.00433  -0.1052   0.1533   1.0000
   4.750   1.0386   0.01208   0.00454  -0.1048   0.1482   1.0000
   5.000   1.0643   0.01231   0.00472  -0.1045   0.1398   1.0000
   5.500   1.1058   0.01403   0.00581  -0.1025   0.0227   1.0000
   5.750   1.1301   0.01443   0.00621  -0.1018   0.0157   1.0000
   6.000   1.1545   0.01480   0.00664  -0.1013   0.0137   1.0000
   6.250   1.1784   0.01524   0.00715  -0.1006   0.0122   1.0000
   6.500   1.2013   0.01580   0.00782  -0.0997   0.0107   1.0000
   6.750   1.2249   0.01622   0.00828  -0.0991   0.0100   1.0000
   7.000   1.2479   0.01670   0.00883  -0.0983   0.0092   1.0000
   7.250   1.2703   0.01727   0.00945  -0.0974   0.0085   1.0000
   7.500   1.2918   0.01790   0.01017  -0.0965   0.0080   1.0000
   7.750   1.3119   0.01868   0.01102  -0.0953   0.0076   1.0000
   8.000   1.3287   0.01979   0.01223  -0.0937   0.0071   1.0000
   8.250   1.3490   0.02042   0.01293  -0.0925   0.0068   1.0000
   8.500   1.3684   0.02112   0.01370  -0.0913   0.0064   1.0000
   8.750   1.3860   0.02194   0.01459  -0.0898   0.0060   1.0000
   9.000   1.4018   0.02287   0.01563  -0.0881   0.0057   1.0000
   9.250   1.4165   0.02383   0.01666  -0.0863   0.0055   1.0000
   9.500   1.4294   0.02485   0.01777  -0.0842   0.0053   1.0000
   9.750   1.4389   0.02593   0.01892  -0.0816   0.0051   1.0000
  10.000   1.4440   0.02723   0.02030  -0.0785   0.0050   1.0000
  10.250   1.4440   0.02894   0.02212  -0.0749   0.0049   1.0000
  10.500   1.4467   0.03057   0.02385  -0.0720   0.0048   1.0000
  10.750   1.4505   0.03219   0.02559  -0.0695   0.0047   1.0000
  11.000   1.4531   0.03404   0.02755  -0.0671   0.0046   1.0000
  11.250   1.4547   0.03608   0.02972  -0.0648   0.0045   1.0000
  11.500   1.4560   0.03827   0.03206  -0.0628   0.0044   1.0000
  11.750   1.4572   0.04057   0.03449  -0.0611   0.0043   1.0000
  12.000   1.4584   0.04295   0.03700  -0.0596   0.0041   1.0000
  12.250   1.4593   0.04545   0.03962  -0.0583   0.0040   1.0000
  12.500   1.4595   0.04807   0.04238  -0.0573   0.0039   1.0000
  12.750   1.4590   0.05089   0.04531  -0.0565   0.0038   1.0000
  13.000   1.4579   0.05387   0.04842  -0.0560   0.0037   1.0000
  13.250   1.4551   0.05715   0.05184  -0.0557   0.0036   1.0000
  13.500   1.4516   0.06067   0.05548  -0.0556   0.0035   1.0000
  13.750   1.4467   0.06448   0.05943  -0.0557   0.0035   1.0000
  14.000   1.4411   0.06848   0.06357  -0.0562   0.0035   1.0000
  14.250   1.4348   0.07276   0.06799  -0.0570   0.0034   1.0000
  14.500   1.4279   0.07730   0.07266  -0.0580   0.0034   1.0000
  14.750   1.4202   0.08210   0.07760  -0.0594   0.0034   1.0000
  15.000   1.4117   0.08718   0.08282  -0.0610   0.0033   1.0000
  15.250   1.4025   0.09254   0.08832  -0.0629   0.0033   1.0000
  15.500   1.3930   0.09814   0.09406  -0.0651   0.0033   1.0000
  15.750   1.3825   0.10401   0.10007  -0.0675   0.0033   1.0000
  16.000   1.3726   0.10997   0.10616  -0.0703   0.0033   1.0000
  16.250   1.3618   0.11624   0.11257  -0.0732   0.0033   1.0000
  16.500   1.3510   0.12268   0.11915  -0.0764   0.0032   1.0000
  16.750   1.3400   0.12930   0.12590  -0.0798   0.0032   1.0000
  17.000   1.3288   0.13614   0.13290  -0.0835   0.0032   1.0000
  17.250   1.3179   0.14314   0.14004  -0.0874   0.0032   1.0000
  17.500   1.3070   0.15040   0.14743  -0.0917   0.0032   1.0000
  17.750   1.2960   0.15795   0.15512  -0.0963   0.0032   1.0000
  18.000   1.2848   0.16584   0.16311  -0.1012   0.0032   1.0000
  18.250   1.2739   0.17396   0.17135  -0.1064   0.0032   1.0000
  18.500   1.2618   0.18289   0.18042  -0.1121   0.0032   1.0000
  18.750   1.2490   0.19264   0.19031  -0.1184   0.0032   1.0000
  19.000   1.2293   0.20595   0.20379  -0.1268   0.0033   1.0000
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