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GOE 257 AIRFOIL (goe257-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 257 AIRFOIL (goe257-il)
Reynolds number: 50,000
Max Cl/Cd: 38.5 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe257-il-50000.txt
Download as CSV file: xf-goe257-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 257 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4232   0.11109   0.10460  -0.0159   1.0000   0.1550
  -8.000  -0.4000   0.10478   0.09827  -0.0135   1.0000   0.1641
  -7.750  -0.4111   0.10368   0.09729  -0.0171   1.0000   0.1694
  -7.500  -0.3963   0.09864   0.09228  -0.0150   1.0000   0.1773
  -7.250  -0.4038   0.09742   0.09116  -0.0217   1.0000   0.1847
  -7.000  -0.3884   0.09238   0.08616  -0.0177   1.0000   0.1953
  -6.500  -0.3787   0.08584   0.07973  -0.0203   1.0000   0.2185
  -6.250  -0.3719   0.08262   0.07658  -0.0201   1.0000   0.2345
  -6.000  -0.3654   0.07956   0.07358  -0.0198   1.0000   0.2526
  -5.750  -0.3633   0.07731   0.07138  -0.0234   1.0000   0.2744
  -5.500  -0.3551   0.07361   0.06778  -0.0187   1.0000   0.2935
  -5.250  -0.3518   0.07104   0.06529  -0.0180   1.0000   0.3207
  -5.000  -0.3485   0.06839   0.06275  -0.0148   1.0000   0.3508
  -4.750  -0.0004   0.04596   0.03929  -0.0217   1.0000   1.0000
  -4.500   0.0122   0.04381   0.03720  -0.0231   1.0000   1.0000
  -4.250   0.0247   0.04175   0.03518  -0.0245   1.0000   1.0000
  -4.000   0.0372   0.03978   0.03327  -0.0259   1.0000   1.0000
  -3.750   0.0085   0.04013   0.03379  -0.0177   1.0000   0.9821
  -3.500  -0.0470   0.04142   0.03538  -0.0045   1.0000   0.9429
  -3.250  -0.0974   0.04203   0.03630   0.0060   1.0000   0.9025
  -3.000  -0.1479   0.04263   0.03721   0.0162   1.0000   0.8765
  -2.750  -0.2004   0.04335   0.03819   0.0267   1.0000   0.8645
  -2.500  -0.2627   0.04418   0.03926   0.0390   1.0000   0.8557
  -2.250  -0.1241   0.03981   0.03242  -0.0472   1.0000   0.2919
  -1.750  -0.0470   0.03659   0.02772  -0.0531   1.0000   0.1941
  -1.500  -0.0137   0.03542   0.02602  -0.0548   0.9986   0.1752
  -1.250   0.0436   0.03393   0.02390  -0.0602   0.9886   0.1606
  -1.000   0.0978   0.03296   0.02237  -0.0651   0.9780   0.1533
  -0.750   0.1504   0.03215   0.02120  -0.0700   0.9674   0.1550
  -0.500   0.2005   0.03136   0.02017  -0.0741   0.9564   0.1563
  -0.250   0.2464   0.03077   0.01944  -0.0775   0.9443   0.1585
   0.000   0.2913   0.03036   0.01895  -0.0809   0.9321   0.1644
   0.250   0.3369   0.03000   0.01856  -0.0845   0.9200   0.1761
   0.500   0.3871   0.02940   0.01821  -0.0891   0.9089   0.2220
   0.750   0.4274   0.02748   0.01795  -0.0907   0.8975   1.0000
   1.000   0.4657   0.02799   0.01799  -0.0927   0.8840   1.0000
   1.250   0.5012   0.02853   0.01827  -0.0945   0.8706   1.0000
   1.500   0.5343   0.02914   0.01869  -0.0960   0.8576   1.0000
   1.750   0.5662   0.02977   0.01919  -0.0972   0.8450   1.0000
   2.000   0.5987   0.03037   0.01971  -0.0983   0.8331   1.0000
   2.250   0.6367   0.03073   0.01999  -0.1001   0.8228   1.0000
   2.500   0.6631   0.03151   0.02074  -0.1003   0.8102   1.0000
   2.750   0.6909   0.03212   0.02135  -0.1003   0.7966   1.0000
   3.000   0.7237   0.03221   0.02142  -0.1002   0.7815   1.0000
   3.250   0.7574   0.03202   0.02123  -0.0996   0.7658   1.0000
   3.500   0.7850   0.03221   0.02142  -0.0985   0.7495   1.0000
   3.750   0.8126   0.03251   0.02178  -0.0975   0.7352   1.0000
   4.000   0.8392   0.03295   0.02227  -0.0966   0.7215   1.0000
   4.250   0.8634   0.03359   0.02298  -0.0956   0.7071   1.0000
   4.500   0.8880   0.03416   0.02368  -0.0945   0.6924   1.0000
   4.750   0.9129   0.03468   0.02428  -0.0933   0.6774   1.0000
   5.000   0.9347   0.03548   0.02520  -0.0920   0.6609   1.0000
   5.250   0.9547   0.03641   0.02628  -0.0906   0.6429   1.0000
   5.500   0.9774   0.03705   0.02709  -0.0891   0.6251   1.0000
   5.750   1.0020   0.03746   0.02764  -0.0875   0.6076   1.0000
   6.000   1.0287   0.03763   0.02794  -0.0859   0.5905   1.0000
   6.250   1.0518   0.03821   0.02867  -0.0844   0.5720   1.0000
   6.500   1.0703   0.03938   0.03008  -0.0830   0.5524   1.0000
   6.750   1.0927   0.04028   0.03116  -0.0817   0.5359   1.0000
   7.000   1.1159   0.04102   0.03208  -0.0804   0.5202   1.0000
   7.250   1.1427   0.04100   0.03223  -0.0789   0.5043   1.0000
   7.500   1.1747   0.03989   0.03128  -0.0769   0.4875   1.0000
   7.750   1.1923   0.04053   0.03219  -0.0750   0.4676   1.0000
   8.000   1.2272   0.03652   0.02811  -0.0711   0.4340   1.0000
   8.250   1.2477   0.03402   0.02558  -0.0671   0.3935   1.0000
   8.500   1.2554   0.03261   0.02423  -0.0625   0.3422   1.0000
   8.750   1.2471   0.03333   0.02468  -0.0569   0.2565   1.0000
   9.000   1.2308   0.03669   0.02733  -0.0518   0.1783   1.0000
   9.250   1.2212   0.03984   0.03008  -0.0479   0.1390   1.0000
   9.500   1.2139   0.04259   0.03259  -0.0444   0.1221   1.0000
   9.750   1.2108   0.04534   0.03521  -0.0416   0.1103   1.0000
  10.000   1.2126   0.04799   0.03782  -0.0392   0.1012   1.0000
  10.250   1.2249   0.05027   0.03999  -0.0369   0.0942   1.0000
  10.500   1.2627   0.05218   0.04201  -0.0355   0.0873   1.0000
  10.750   1.3135   0.05576   0.04575  -0.0367   0.0812   1.0000
  11.000   1.3294   0.05916   0.04954  -0.0355   0.0783   1.0000
  11.250   1.3414   0.06295   0.05372  -0.0341   0.0769   1.0000
  11.500   1.3421   0.06689   0.05807  -0.0319   0.0769   1.0000
  11.750   1.3328   0.07084   0.06242  -0.0293   0.0772   1.0000
  12.000   1.3181   0.07509   0.06702  -0.0272   0.0777   1.0000
  12.250   1.2990   0.07976   0.07203  -0.0260   0.0783   1.0000
  12.500   1.2767   0.08499   0.07755  -0.0259   0.0789   1.0000
  12.750   1.2520   0.09089   0.08372  -0.0270   0.0797   1.0000
  13.000   1.2255   0.09756   0.09061  -0.0293   0.0804   1.0000
  13.250   1.1984   0.10501   0.09824  -0.0327   0.0813   1.0000
  13.500   1.1728   0.11310   0.10645  -0.0368   0.0823   1.0000
  13.750   1.1523   0.12130   0.11473  -0.0409   0.0832   1.0000
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