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GOE 264 AIRFOIL (goe264-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 264 AIRFOIL (goe264-il)
Reynolds number: 100,000
Max Cl/Cd: 59.94 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe264-il-100000.txt
Download as CSV file: xf-goe264-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 264 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3093   0.10425   0.09946  -0.0228   1.0000   0.0580
  -7.750  -0.3129   0.10394   0.09926  -0.0248   1.0000   0.0588
  -7.500  -0.3122   0.10364   0.09904  -0.0294   1.0000   0.0593
  -7.250  -0.3075   0.10276   0.09821  -0.0343   1.0000   0.0595
  -7.000  -0.3034   0.09878   0.09430  -0.0347   1.0000   0.0599
  -6.750  -0.3012   0.09214   0.08771  -0.0273   1.0000   0.0611
  -6.500  -0.2981   0.08891   0.08453  -0.0251   1.0000   0.0624
  -6.250  -0.2958   0.08644   0.08211  -0.0242   1.0000   0.0639
  -6.000  -0.2933   0.08417   0.07986  -0.0241   1.0000   0.0657
  -5.750  -0.2893   0.08197   0.07771  -0.0247   1.0000   0.0682
  -5.500  -0.2707   0.08123   0.07692  -0.0328   1.0000   0.0725
  -5.250  -0.2528   0.07848   0.07412  -0.0388   1.0000   0.0737
  -5.000  -0.2567   0.07438   0.07012  -0.0339   1.0000   0.0748
  -4.750  -0.2531   0.07151   0.06731  -0.0318   1.0000   0.0766
  -4.500  -0.2435   0.06902   0.06483  -0.0322   1.0000   0.0793
  -4.250  -0.1865   0.06900   0.06440  -0.0475   1.0000   0.0871
  -4.000  -0.1884   0.06340   0.05902  -0.0439   0.9987   0.0885
  -3.750  -0.1241   0.06042   0.05573  -0.0555   0.9912   0.1007
  -3.500  -0.0881   0.05450   0.04983  -0.0605   0.9847   0.1040
  -3.250  -0.0259   0.05113   0.04616  -0.0710   0.9763   0.1169
  -2.750   0.0686   0.04367   0.03846  -0.0833   0.9604   0.1362
  -2.500   0.1227   0.04061   0.03520  -0.0905   0.9528   0.1519
  -2.250   0.1834   0.03840   0.03262  -0.0985   0.9442   0.1733
  -2.000   0.2302   0.03529   0.02940  -0.1036   0.9351   0.1888
  -0.750   0.4672   0.02421   0.01659  -0.1208   0.8761   0.1426
  -0.500   0.5010   0.02269   0.01484  -0.1211   0.8597   0.1413
  -0.250   0.5334   0.02121   0.01304  -0.1209   0.8428   0.1350
   0.000   0.5640   0.02006   0.01153  -0.1202   0.8254   0.1326
   0.250   0.5913   0.01927   0.01057  -0.1193   0.8047   0.1345
   0.500   0.6184   0.01871   0.00982  -0.1183   0.7845   0.1410
   0.750   0.6451   0.01816   0.00915  -0.1173   0.7654   0.1500
   1.000   0.6715   0.01775   0.00857  -0.1163   0.7436   0.1577
   1.250   0.6977   0.01727   0.00803  -0.1154   0.7241   0.1698
   1.500   0.7230   0.01691   0.00766  -0.1142   0.7047   0.1929
   1.750   0.7494   0.01656   0.00732  -0.1135   0.6852   0.2386
   2.000   0.7740   0.01520   0.00709  -0.1128   0.6678   0.6907
   2.250   0.7968   0.01510   0.00686  -0.1107   0.6509   1.0000
   2.500   0.8237   0.01549   0.00696  -0.1102   0.6343   1.0000
   2.750   0.8505   0.01591   0.00721  -0.1098   0.6181   1.0000
   3.000   0.8773   0.01635   0.00751  -0.1095   0.6028   1.0000
   3.250   0.9041   0.01681   0.00783  -0.1092   0.5885   1.0000
   3.500   0.9308   0.01726   0.00822  -0.1089   0.5748   1.0000
   3.750   0.9574   0.01771   0.00864  -0.1087   0.5616   1.0000
   4.000   0.9840   0.01820   0.00913  -0.1085   0.5496   1.0000
   4.250   1.0108   0.01870   0.00962  -0.1083   0.5389   1.0000
   4.750   1.0640   0.01969   0.01067  -0.1080   0.5189   1.0000
   5.000   1.0905   0.02024   0.01128  -0.1078   0.5099   1.0000
   5.250   1.1174   0.02078   0.01185  -0.1076   0.5022   1.0000
   5.500   1.1434   0.02143   0.01267  -0.1075   0.4938   1.0000
   5.750   1.1703   0.02196   0.01323  -0.1073   0.4868   1.0000
   6.000   1.1955   0.02264   0.01412  -0.1071   0.4782   1.0000
   6.250   1.2226   0.02311   0.01459  -0.1068   0.4711   1.0000
   6.500   1.2471   0.02325   0.01483  -0.1060   0.4568   1.0000
   6.750   1.2683   0.02282   0.01443  -0.1043   0.4316   1.0000
   7.000   1.2904   0.02260   0.01419  -0.1029   0.4094   1.0000
   7.250   1.3111   0.02243   0.01410  -0.1013   0.3852   1.0000
   7.500   1.3282   0.02216   0.01403  -0.0992   0.3479   1.0000
   7.750   1.3297   0.02336   0.01436  -0.0951   0.1572   1.0000
   8.000   1.3264   0.02719   0.01738  -0.0914   0.0817   1.0000
   8.250   1.3344   0.02928   0.01948  -0.0887   0.0692   1.0000
   8.500   1.3415   0.03116   0.02149  -0.0859   0.0623   1.0000
   8.750   1.3434   0.03321   0.02363  -0.0827   0.0581   1.0000
   9.000   1.3404   0.03547   0.02591  -0.0788   0.0560   1.0000
   9.250   1.3442   0.03723   0.02779  -0.0755   0.0544   1.0000
   9.500   1.3529   0.03912   0.02973  -0.0728   0.0526   1.0000
   9.750   1.3677   0.04107   0.03174  -0.0708   0.0500   1.0000
  10.000   1.3900   0.04346   0.03403  -0.0700   0.0467   1.0000
  10.250   1.4510   0.04902   0.03948  -0.0740   0.0448   1.0000
  10.500   1.4754   0.05263   0.04336  -0.0734   0.0447   1.0000
  10.750   1.4952   0.05644   0.04751  -0.0724   0.0449   1.0000
  11.000   1.5071   0.06045   0.05191  -0.0708   0.0449   1.0000
  11.250   1.5096   0.06415   0.05597  -0.0683   0.0446   1.0000
  11.500   1.5069   0.06730   0.05950  -0.0653   0.0445   1.0000
  11.750   1.5114   0.07229   0.06482  -0.0636   0.0449   1.0000
  12.000   1.5054   0.07354   0.06638  -0.0600   0.0455   1.0000
  12.250   1.4873   0.07506   0.06826  -0.0553   0.0464   1.0000
  12.500   1.4564   0.07819   0.07181  -0.0518   0.0473   1.0000
  12.750   1.4261   0.08270   0.07671  -0.0503   0.0483   1.0000
  13.000   1.3986   0.08810   0.08244  -0.0503   0.0494   1.0000
  13.250   1.3724   0.09410   0.08873  -0.0517   0.0502   1.0000
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