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GOE 535 AIRFOIL (goe535-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 535 AIRFOIL (goe535-il)
Reynolds number: 50,000
Max Cl/Cd: 7.15 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe535-il-50000.txt
Download as CSV file: xf-goe535-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 535 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.1859   0.12530   0.11844  -0.0260   1.0000   0.2415
  -9.250  -0.2009   0.12558   0.11885  -0.0242   1.0000   0.2479
  -9.000  -0.2435   0.12937   0.12285  -0.0218   1.0000   0.2503
  -8.750  -0.2147   0.12280   0.11633  -0.0198   1.0000   0.2543
  -8.500  -0.2145   0.12134   0.11497  -0.0171   1.0000   0.2600
  -8.250  -0.2332   0.12192   0.11568  -0.0143   1.0000   0.2660
  -8.000  -0.2765   0.12526   0.11921  -0.0114   1.0000   0.2690
  -7.750  -0.2620   0.12095   0.11498  -0.0093   1.0000   0.2730
  -7.500  -0.2616   0.11957   0.11368  -0.0068   1.0000   0.2788
  -7.250  -0.2814   0.12016   0.11439  -0.0044   1.0000   0.2852
  -7.000  -0.3288   0.12345   0.11785  -0.0018   1.0000   0.2883
  -6.750  -0.2633   0.11564   0.10997  -0.0069   0.9923   0.2986
  -6.500  -0.2626   0.11465   0.10901  -0.0130   0.9800   0.3093
  -6.250  -0.2159   0.10977   0.10408  -0.0175   0.9687   0.3232
  -6.000  -0.1909   0.10623   0.10054  -0.0217   0.9564   0.3335
  -5.750  -0.2051   0.10733   0.10169  -0.0238   0.9409   0.3465
  -5.500  -0.1367   0.10004   0.09432  -0.0303   0.9336   0.3594
  -5.250  -0.1672   0.10149   0.09587  -0.0302   0.9168   0.3685
  -5.000  -0.1135   0.09574   0.09006  -0.0331   0.9051   0.3812
  -4.750  -0.1402   0.09651   0.09091  -0.0324   0.8892   0.3898
  -4.500  -0.0861   0.09126   0.08558  -0.0366   0.8805   0.4041
  -4.250  -0.1095   0.09142   0.08581  -0.0354   0.8642   0.4115
  -4.000  -0.1158   0.06139   0.05460  -0.0914   0.8552   0.2132
  -3.750  -0.0800   0.05591   0.04862  -0.0992   0.8439   0.2123
  -3.500  -0.0464   0.05274   0.04520  -0.1032   0.8331   0.2148
  -3.250  -0.0119   0.05129   0.04370  -0.1051   0.8223   0.2205
  -3.000   0.0181   0.04904   0.04104  -0.1082   0.8110   0.2250
  -2.750   0.0652   0.04635   0.03773  -0.1131   0.8015   0.2329
  -2.500   0.0837   0.04620   0.03761  -0.1124   0.7898   0.2389
  -2.250   0.1279   0.04475   0.03569  -0.1155   0.7808   0.2504
  -2.000   0.1430   0.04501   0.03610  -0.1141   0.7696   0.2574
  -1.750   0.1829   0.04425   0.03517  -0.1159   0.7605   0.2722
  -1.500   0.1993   0.04476   0.03571  -0.1147   0.7504   0.2835
  -1.250   0.2258   0.04491   0.03593  -0.1145   0.7410   0.3010
  -1.000   0.2587   0.04500   0.03603  -0.1149   0.7330   0.3283
  -0.750   0.2636   0.04632   0.03748  -0.1125   0.7223   0.3490
  -0.500   0.3065   0.04650   0.03803  -0.1119   0.7160   0.4164
  -0.250   0.2891   0.04896   0.04058  -0.1076   0.7055   0.4378
   0.000   0.3075   0.04999   0.04178  -0.1043   0.6980   0.5052
   0.250   0.3233   0.05101   0.04277  -0.1016   0.6910   0.5559
   0.500   0.3151   0.05299   0.04476  -0.0985   0.6825   0.5774
   0.750   0.3409   0.05322   0.04496  -0.0969   0.6759   0.6171
   1.000   0.3487   0.05448   0.04620  -0.0948   0.6690   0.6415
   1.250   0.3447   0.05636   0.04807  -0.0926   0.6617   0.6598
   1.500   0.3636   0.05684   0.04857  -0.0904   0.6555   0.6989
   1.750   0.3804   0.05747   0.04923  -0.0882   0.6496   0.7377
   2.000   0.3679   0.06000   0.05177  -0.0863   0.6435   0.7531
   2.250   0.3774   0.06123   0.05305  -0.0849   0.6378   0.7801
   2.500   0.4329   0.06054   0.05230  -0.0860   0.6305   0.8198
   2.750   0.4113   0.06397   0.05580  -0.0849   0.6258   0.8306
   3.000   0.4163   0.06618   0.05811  -0.0854   0.6211   0.8523
   3.250   0.4575   0.06735   0.05943  -0.0890   0.6135   0.9052
   3.500   0.3116   0.07989   0.07226  -0.0884   0.7543   0.8476
   3.750   0.3397   0.08101   0.07361  -0.0911   0.7391   0.9607
   4.000   0.3510   0.08318   0.07564  -0.0917   0.7313   1.0000
   4.250   0.3875   0.08599   0.07826  -0.0953   0.7176   1.0000
   4.500   0.3954   0.08799   0.08017  -0.0959   0.7079   1.0000
   4.750   0.4411   0.09165   0.08363  -0.1003   0.6953   1.0000
   5.000   0.4379   0.09300   0.08492  -0.0995   0.6840   1.0000
   5.250   0.4883   0.09736   0.08908  -0.1040   0.6736   1.0000
   5.500   0.4780   0.09821   0.08990  -0.1024   0.6609   1.0000
   5.750   0.5291   0.10302   0.09452  -0.1066   0.6522   1.0000
   6.000   0.5129   0.10356   0.09504  -0.1046   0.6397   1.0000
   6.250   0.5647   0.10860   0.09990  -0.1083   0.6310   1.0000
   6.500   0.5447   0.10894   0.10024  -0.1062   0.6186   1.0000
   6.750   0.5857   0.11331   0.10447  -0.1087   0.6109   1.0000
   7.000   0.5720   0.11444   0.10559  -0.1073   0.6000   1.0000
   7.250   0.6075   0.11826   0.10929  -0.1091   0.5909   1.0000
   7.500   0.5997   0.12007   0.11107  -0.1083   0.5818   1.0000
   7.750   0.6208   0.12298   0.11392  -0.1091   0.5725   1.0000
   8.000   0.6558   0.12821   0.11905  -0.1110   0.5679   1.0000
   8.250   0.6377   0.12815   0.11900  -0.1095   0.5550   1.0000
   8.500   0.6765   0.13298   0.12375  -0.1111   0.5489   1.0000
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