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GOE 265 AIRFOIL (goe265-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 265 AIRFOIL (goe265-il)
Reynolds number: 200,000
Max Cl/Cd: 79.26 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe265-il-200000.txt
Download as CSV file: xf-goe265-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 265 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2402   0.10526   0.10197  -0.0183   1.0000   0.0361
  -8.250  -0.2369   0.10408   0.10086  -0.0218   1.0000   0.0369
  -8.000  -0.2412   0.10380   0.10069  -0.0250   1.0000   0.0371
  -7.750  -0.2245   0.09760   0.09450  -0.0231   1.0000   0.0376
  -7.500  -0.2167   0.09473   0.09168  -0.0225   1.0000   0.0383
  -7.250  -0.2194   0.09324   0.09031  -0.0211   1.0000   0.0389
  -7.000  -0.1964   0.08963   0.08672  -0.0263   0.9880   0.0402
  -6.750  -0.1635   0.08538   0.08244  -0.0348   0.9706   0.0425
  -6.500  -0.1082   0.08197   0.07892  -0.0581   0.9425   0.0441
  -6.250  -0.0990   0.07683   0.07378  -0.0531   0.9269   0.0447
  -6.000  -0.0837   0.07375   0.07065  -0.0526   0.9060   0.0459
  -5.750  -0.0665   0.07121   0.06804  -0.0543   0.8836   0.0480
  -5.500  -0.0389   0.06864   0.06533  -0.0607   0.8632   0.0513
  -5.250   0.0023   0.06502   0.06151  -0.0731   0.8451   0.0526
  -5.000   0.0098   0.06180   0.05826  -0.0697   0.8293   0.0533
  -4.750   0.0259   0.05925   0.05563  -0.0695   0.8136   0.0546
  -4.500   0.0493   0.05685   0.05311  -0.0716   0.7979   0.0577
  -4.250   0.1099   0.05337   0.04929  -0.0861   0.7827   0.0623
  -4.000   0.1214   0.05034   0.04623  -0.0841   0.7687   0.0632
  -3.750   0.1410   0.04803   0.04385  -0.0841   0.7557   0.0649
  -3.500   0.2013   0.04696   0.04233  -0.0941   0.7434   0.0729
  -3.250   0.2235   0.04272   0.03799  -0.0956   0.7331   0.0740
  -3.000   0.2422   0.04033   0.03559  -0.0952   0.7217   0.0753
  -2.750   0.2670   0.03847   0.03363  -0.0958   0.7116   0.0778
  -2.500   0.3215   0.03689   0.03152  -0.1024   0.7014   0.0864
  -2.250   0.3416   0.03400   0.02867  -0.1025   0.6914   0.0877
  -2.000   0.3661   0.03231   0.02688  -0.1027   0.6825   0.0898
  -1.750   0.4124   0.03244   0.02648  -0.1057   0.6719   0.1000
  -1.500   0.4346   0.02891   0.02300  -0.1064   0.6636   0.1019
  -1.250   0.4606   0.02740   0.02144  -0.1067   0.6540   0.1043
  -1.000   0.5003   0.02761   0.02110  -0.1079   0.6447   0.1148
  -0.750   0.5244   0.02468   0.01823  -0.1086   0.6363   0.1173
  -0.500   0.5673   0.02015   0.01278  -0.1103   0.6285   0.0857
  -0.250   0.5971   0.01832   0.01061  -0.1107   0.6201   0.0873
   0.000   0.6237   0.01821   0.01058  -0.1106   0.6100   0.0923
   0.250   0.6533   0.01726   0.00927  -0.1105   0.6019   0.0964
   0.500   0.6825   0.01642   0.00818  -0.1104   0.5920   0.1022
   0.750   0.7098   0.01628   0.00800  -0.1101   0.5830   0.1096
   1.000   0.7381   0.01580   0.00731  -0.1099   0.5733   0.1170
   1.250   0.7654   0.01567   0.00716  -0.1096   0.5631   0.1256
   1.500   0.7930   0.01542   0.00674  -0.1093   0.5541   0.1332
   1.750   0.8204   0.01529   0.00661  -0.1090   0.5432   0.1413
   2.000   0.8477   0.01511   0.00636  -0.1087   0.5334   0.1482
   2.250   0.8748   0.01507   0.00624  -0.1084   0.5237   0.1563
   2.500   0.9017   0.01491   0.00611  -0.1080   0.5123   0.1626
   2.750   0.9285   0.01490   0.00607  -0.1077   0.5011   0.1718
   3.000   0.9551   0.01485   0.00597  -0.1073   0.4904   0.1805
   3.250   0.9817   0.01481   0.00596  -0.1069   0.4784   0.1902
   3.500   1.0083   0.01483   0.00602  -0.1066   0.4674   0.2040
   3.750   1.0347   0.01487   0.00606  -0.1062   0.4582   0.2227
   4.000   1.0610   0.01487   0.00619  -0.1058   0.4481   0.2568
   4.250   1.0868   0.01395   0.00629  -0.1053   0.4395   1.0000
   4.500   1.1132   0.01420   0.00642  -0.1049   0.4307   1.0000
   4.750   1.1395   0.01448   0.00665  -0.1046   0.4222   1.0000
   5.000   1.1655   0.01477   0.00684  -0.1042   0.4143   1.0000
   5.250   1.1916   0.01506   0.00713  -0.1038   0.4063   1.0000
   5.500   1.2175   0.01537   0.00739  -0.1035   0.3994   1.0000
   5.750   1.2434   0.01571   0.00772  -0.1031   0.3926   1.0000
   6.000   1.2690   0.01601   0.00803  -0.1027   0.3855   1.0000
   6.250   1.2945   0.01638   0.00836  -0.1023   0.3791   1.0000
   6.500   1.3197   0.01668   0.00870  -0.1019   0.3716   1.0000
   6.750   1.3450   0.01708   0.00904  -0.1015   0.3654   1.0000
   7.000   1.3698   0.01739   0.00947  -0.1011   0.3584   1.0000
   7.250   1.3946   0.01778   0.00981  -0.1006   0.3521   1.0000
   7.500   1.4192   0.01815   0.01028  -0.1001   0.3457   1.0000
   7.750   1.4436   0.01851   0.01071  -0.0996   0.3394   1.0000
   8.000   1.4679   0.01897   0.01116  -0.0991   0.3336   1.0000
   8.250   1.4915   0.01932   0.01165  -0.0985   0.3267   1.0000
   8.500   1.5153   0.01978   0.01207  -0.0980   0.3204   1.0000
   8.750   1.5379   0.02015   0.01263  -0.0973   0.3130   1.0000
   9.000   1.5605   0.02057   0.01306  -0.0966   0.3055   1.0000
   9.250   1.5814   0.02091   0.01357  -0.0956   0.2954   1.0000
   9.500   1.6014   0.02129   0.01403  -0.0946   0.2839   1.0000
   9.750   1.6203   0.02170   0.01448  -0.0934   0.2713   1.0000
  10.000   1.6382   0.02217   0.01502  -0.0921   0.2576   1.0000
  10.250   1.6549   0.02271   0.01564  -0.0907   0.2412   1.0000
  10.500   1.6698   0.02338   0.01637  -0.0891   0.2231   1.0000
  10.750   1.6822   0.02425   0.01724  -0.0873   0.2059   1.0000
  11.000   1.6925   0.02527   0.01824  -0.0852   0.1910   1.0000
  11.250   1.6991   0.02637   0.01934  -0.0827   0.1787   1.0000
  11.500   1.7037   0.02763   0.02062  -0.0801   0.1685   1.0000
  11.750   1.7058   0.02918   0.02216  -0.0777   0.1604   1.0000
  12.000   1.7105   0.03070   0.02378  -0.0758   0.1526   1.0000
  12.250   1.7100   0.03275   0.02584  -0.0740   0.1455   1.0000
  12.500   1.7110   0.03486   0.02803  -0.0726   0.1376   1.0000
  12.750   1.7091   0.03739   0.03061  -0.0715   0.1313   1.0000
  13.000   1.7086   0.03995   0.03328  -0.0707   0.1245   1.0000
  13.250   1.7037   0.04310   0.03649  -0.0701   0.1182   1.0000
  13.500   1.7002   0.04628   0.03980  -0.0698   0.1098   1.0000
  13.750   1.6953   0.04977   0.04341  -0.0698   0.0991   1.0000
  14.000   1.6866   0.05389   0.04758  -0.0701   0.0822   1.0000
  14.250   1.6686   0.05923   0.05284  -0.0706   0.0615   1.0000
  14.500   1.6465   0.06520   0.05876  -0.0714   0.0518   1.0000
  14.750   1.6263   0.07111   0.06471  -0.0722   0.0456   1.0000
  15.000   1.6071   0.07714   0.07080  -0.0734   0.0415   1.0000
  15.250   1.5902   0.08301   0.07676  -0.0746   0.0386   1.0000
  15.500   1.5726   0.08917   0.08301  -0.0760   0.0366   1.0000
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