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GOE 533 AIRFOIL (goe533-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 533 AIRFOIL (goe533-il)
Reynolds number: 1,000,000
Max Cl/Cd: 131.08 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe533-il-1000000.txt
Download as CSV file: xf-goe533-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 533 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.1324   0.06918   0.06740  -0.0763   0.9189   0.0274
  -9.750  -0.4030   0.04223   0.04017  -0.1013   0.9614   0.0268
  -9.500  -0.3719   0.03822   0.03599  -0.1098   0.9416   0.0271
  -9.250  -0.3527   0.03557   0.03311  -0.1131   0.9030   0.0273
  -9.000  -0.3440   0.03385   0.03110  -0.1126   0.8556   0.0275
  -8.750  -0.3350   0.03230   0.02927  -0.1116   0.8094   0.0277
  -8.500  -0.3232   0.03095   0.02764  -0.1106   0.7685   0.0280
  -8.250  -0.3044   0.03048   0.02701  -0.1099   0.7366   0.0286
  -8.000  -0.3219   0.01949   0.01444  -0.1089   0.7185   0.0268
  -7.750  -0.3008   0.01795   0.01269  -0.1084   0.7007   0.0271
  -7.500  -0.2766   0.01716   0.01176  -0.1080   0.6865   0.0274
  -7.250  -0.2515   0.01658   0.01109  -0.1077   0.6753   0.0277
  -6.750  -0.1999   0.01552   0.00984  -0.1071   0.6574   0.0283
  -6.500  -0.1738   0.01507   0.00930  -0.1068   0.6495   0.0288
  -6.250  -0.1473   0.01455   0.00868  -0.1066   0.6430   0.0292
  -6.000  -0.1209   0.01392   0.00795  -0.1063   0.6365   0.0295
  -5.750  -0.0945   0.01343   0.00734  -0.1060   0.6301   0.0298
  -5.500  -0.0673   0.01294   0.00679  -0.1058   0.6251   0.0301
  -5.250  -0.0401   0.01254   0.00631  -0.1056   0.6196   0.0304
  -5.000  -0.0130   0.01222   0.00592  -0.1053   0.6144   0.0307
  -4.750   0.0146   0.01196   0.00560  -0.1051   0.6097   0.0309
  -4.500   0.0407   0.01115   0.00477  -0.1049   0.6051   0.0315
  -4.250   0.0677   0.01077   0.00437  -0.1047   0.6002   0.0321
  -4.000   0.0950   0.01054   0.00412  -0.1045   0.5954   0.0327
  -3.750   0.1228   0.01029   0.00386  -0.1044   0.5914   0.0332
  -3.500   0.1508   0.01005   0.00360  -0.1043   0.5867   0.0338
  -3.250   0.1785   0.00985   0.00336  -0.1041   0.5816   0.0343
  -3.000   0.2062   0.00970   0.00316  -0.1039   0.5764   0.0349
  -2.750   0.2346   0.00951   0.00297  -0.1039   0.5723   0.0355
  -2.500   0.2628   0.00938   0.00281  -0.1038   0.5673   0.0359
  -2.250   0.2903   0.00910   0.00249  -0.1036   0.5621   0.0371
  -2.000   0.3185   0.00896   0.00234  -0.1036   0.5571   0.0383
  -1.750   0.3469   0.00885   0.00223  -0.1035   0.5514   0.0399
  -1.500   0.3750   0.00878   0.00212  -0.1034   0.5454   0.0411
  -1.250   0.4032   0.00867   0.00198  -0.1033   0.5397   0.0431
  -1.000   0.4315   0.00857   0.00188  -0.1033   0.5324   0.0461
  -0.750   0.4594   0.00851   0.00179  -0.1031   0.5249   0.0519
  -0.500   0.4872   0.00821   0.00171  -0.1031   0.5171   0.1203
  -0.250   0.5134   0.00769   0.00164  -0.1031   0.5089   0.2946
   0.000   0.5404   0.00730   0.00167  -0.1031   0.5009   0.4485
   0.250   0.5678   0.00730   0.00170  -0.1029   0.4922   0.4900
   0.500   0.5958   0.00727   0.00173  -0.1028   0.4836   0.5179
   0.750   0.6233   0.00731   0.00177  -0.1026   0.4748   0.5418
   1.000   0.6508   0.00730   0.00182  -0.1024   0.4656   0.5729
   1.250   0.6780   0.00733   0.00190  -0.1022   0.4565   0.6129
   1.500   0.7052   0.00738   0.00200  -0.1020   0.4473   0.6503
   1.750   0.7324   0.00744   0.00209  -0.1017   0.4390   0.6800
   2.000   0.7595   0.00754   0.00217  -0.1015   0.4298   0.6956
   2.250   0.7870   0.00762   0.00224  -0.1013   0.4217   0.7073
   2.750   0.8413   0.00780   0.00240  -0.1009   0.4063   0.7330
   3.000   0.8682   0.00789   0.00250  -0.1006   0.3991   0.7454
   3.250   0.8950   0.00797   0.00259  -0.1003   0.3927   0.7611
   3.500   0.9217   0.00801   0.00269  -0.1000   0.3864   0.7832
   3.750   0.9468   0.00806   0.00281  -0.0994   0.3799   0.8181
   4.000   0.9802   0.00786   0.00291  -0.1005   0.3738   1.0000
   4.250   1.0072   0.00801   0.00302  -0.1003   0.3673   1.0000
   4.500   1.0338   0.00818   0.00315  -0.1001   0.3613   1.0000
   4.750   1.0610   0.00830   0.00326  -0.1000   0.3559   1.0000
   5.000   1.0873   0.00849   0.00340  -0.0997   0.3488   1.0000
   5.250   1.1140   0.00863   0.00353  -0.0995   0.3428   1.0000
   5.500   1.1404   0.00880   0.00367  -0.0992   0.3360   1.0000
   5.750   1.1662   0.00900   0.00383  -0.0989   0.3296   1.0000
   6.000   1.1929   0.00913   0.00397  -0.0987   0.3244   1.0000
   6.250   1.2187   0.00932   0.00414  -0.0984   0.3186   1.0000
   6.500   1.2444   0.00951   0.00431  -0.0980   0.3126   1.0000
   6.750   1.2702   0.00969   0.00448  -0.0977   0.3061   1.0000
   7.000   1.2949   0.00993   0.00468  -0.0972   0.2988   1.0000
   7.250   1.3206   0.01010   0.00486  -0.0969   0.2915   1.0000
   7.500   1.3446   0.01037   0.00509  -0.0963   0.2828   1.0000
   7.750   1.3694   0.01058   0.00529  -0.0959   0.2741   1.0000
   8.000   1.3930   0.01086   0.00554  -0.0952   0.2640   1.0000
   8.250   1.4153   0.01121   0.00582  -0.0944   0.2497   1.0000
   8.500   1.4365   0.01162   0.00615  -0.0934   0.2329   1.0000
   8.750   1.4549   0.01217   0.00658  -0.0920   0.2116   1.0000
   9.000   1.4723   0.01274   0.00705  -0.0905   0.1941   1.0000
   9.500   1.5087   0.01369   0.00791  -0.0876   0.1744   1.0000
   9.750   1.5261   0.01415   0.00834  -0.0860   0.1683   1.0000
  10.000   1.5438   0.01448   0.00870  -0.0844   0.1640   1.0000
  10.250   1.5585   0.01491   0.00912  -0.0823   0.1587   1.0000
  10.500   1.5712   0.01542   0.00962  -0.0799   0.1529   1.0000
  10.750   1.5876   0.01579   0.01002  -0.0782   0.1474   1.0000
  11.000   1.5981   0.01642   0.01062  -0.0757   0.1395   1.0000
  11.250   1.6107   0.01699   0.01117  -0.0736   0.1293   1.0000
  11.500   1.6039   0.01851   0.01245  -0.0691   0.0948   1.0000
  11.750   1.5972   0.02016   0.01400  -0.0651   0.0775   1.0000
  12.000   1.5991   0.02149   0.01533  -0.0624   0.0705   1.0000
  12.250   1.6048   0.02271   0.01658  -0.0604   0.0670   1.0000
  12.500   1.6084   0.02415   0.01805  -0.0584   0.0635   1.0000
  12.750   1.6153   0.02547   0.01942  -0.0569   0.0611   1.0000
  13.000   1.6217   0.02692   0.02092  -0.0556   0.0590   1.0000
  13.250   1.6256   0.02865   0.02269  -0.0543   0.0569   1.0000
  13.500   1.6286   0.03058   0.02466  -0.0532   0.0549   1.0000
  13.750   1.6328   0.03249   0.02664  -0.0524   0.0532   1.0000
  14.000   1.6394   0.03425   0.02847  -0.0517   0.0519   1.0000
  14.250   1.6437   0.03630   0.03058  -0.0511   0.0505   1.0000
  14.500   1.6452   0.03867   0.03300  -0.0506   0.0488   1.0000
  14.750   1.6443   0.04134   0.03572  -0.0502   0.0470   1.0000
  15.000   1.6458   0.04381   0.03826  -0.0499   0.0454   1.0000
  15.250   1.6489   0.04616   0.04068  -0.0496   0.0440   1.0000
  15.500   1.6484   0.04894   0.04352  -0.0495   0.0421   1.0000
  15.750   1.6446   0.05218   0.04679  -0.0495   0.0401   1.0000
  16.000   1.6443   0.05509   0.04976  -0.0496   0.0381   1.0000
  16.250   1.6412   0.05840   0.05312  -0.0498   0.0355   1.0000
  16.500   1.6355   0.06214   0.05691  -0.0502   0.0330   1.0000
  16.750   1.6296   0.06602   0.06083  -0.0508   0.0298   1.0000
  17.000   1.6224   0.07018   0.06505  -0.0515   0.0273   1.0000
  17.250   1.6128   0.07478   0.06970  -0.0525   0.0247   1.0000
  17.500   1.6044   0.07935   0.07433  -0.0536   0.0228   1.0000
  17.750   1.5939   0.08430   0.07934  -0.0550   0.0212   1.0000
  18.000   1.5846   0.08921   0.08433  -0.0564   0.0201   1.0000
  18.250   1.5766   0.09401   0.08921  -0.0579   0.0193   1.0000
  18.500   1.5665   0.09921   0.09449  -0.0597   0.0185   1.0000
  18.750   1.5560   0.10455   0.09991  -0.0617   0.0178   1.0000
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