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GOE 633 AIRFOIL (goe633-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 633 AIRFOIL (goe633-il)
Reynolds number: 50,000
Max Cl/Cd: 26.5 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe633-il-50000-n5.txt
Download as CSV file: xf-goe633-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 633 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3152   0.10412   0.09698  -0.0340   1.0000   0.0813
  -9.750  -0.3156   0.10028   0.09322  -0.0359   1.0000   0.0809
  -9.500  -0.3174   0.09636   0.08939  -0.0378   1.0000   0.0806
  -9.250  -0.3219   0.09220   0.08533  -0.0400   1.0000   0.0801
  -9.000  -0.3500   0.08488   0.07816  -0.0454   1.0000   0.0780
  -8.750  -0.3585   0.08158   0.07500  -0.0464   1.0000   0.0777
  -8.500  -0.3721   0.07838   0.07196  -0.0475   0.9884   0.0773
  -8.250  -0.3687   0.07193   0.06543  -0.0547   0.9577   0.0768
  -8.000  -0.3688   0.06415   0.05746  -0.0622   0.9373   0.0763
  -7.750  -0.3732   0.05695   0.04992  -0.0671   0.9197   0.0760
  -7.500  -0.3741   0.05110   0.04362  -0.0696   0.9050   0.0760
  -7.250  -0.3725   0.04647   0.03847  -0.0700   0.8910   0.0765
  -7.000  -0.3666   0.04258   0.03395  -0.0696   0.8791   0.0777
  -6.750  -0.3459   0.04083   0.03202  -0.0695   0.8698   0.0794
  -6.500  -0.3288   0.03935   0.03034  -0.0687   0.8591   0.0812
  -6.250  -0.3089   0.03749   0.02813  -0.0681   0.8509   0.0833
  -6.000  -0.2927   0.03577   0.02606  -0.0668   0.8407   0.0850
  -5.750  -0.2704   0.03398   0.02381  -0.0661   0.8336   0.0872
  -5.500  -0.2513   0.03288   0.02254  -0.0649   0.8240   0.0893
  -5.250  -0.2270   0.03198   0.02153  -0.0643   0.8170   0.0925
  -5.000  -0.2065   0.03115   0.02049  -0.0632   0.8081   0.0973
  -4.750  -0.1821   0.03034   0.01958  -0.0625   0.8011   0.1034
  -4.500  -0.1593   0.02965   0.01875  -0.0617   0.7932   0.1113
  -4.250  -0.1352   0.02902   0.01813  -0.0609   0.7857   0.1208
  -4.000  -0.1102   0.02852   0.01765  -0.0603   0.7789   0.1366
  -3.750  -0.0874   0.02840   0.01757  -0.0594   0.7707   0.1592
  -3.500  -0.0618   0.02840   0.01744  -0.0587   0.7646   0.1851
  -3.250  -0.0422   0.02863   0.01759  -0.0574   0.7558   0.2071
  -3.000  -0.0216   0.02892   0.01788  -0.0559   0.7490   0.2323
  -2.750  -0.0034   0.02922   0.01813  -0.0543   0.7409   0.2573
  -2.500   0.0200   0.02920   0.01802  -0.0534   0.7333   0.2778
  -2.250   0.0494   0.02892   0.01766  -0.0534   0.7265   0.2924
  -2.000   0.0774   0.02873   0.01737  -0.0534   0.7172   0.3041
  -1.750   0.1120   0.02832   0.01679  -0.0540   0.7109   0.3181
  -1.500   0.1365   0.02830   0.01671  -0.0536   0.7000   0.3315
  -1.250   0.1687   0.02790   0.01625  -0.0537   0.6932   0.3469
  -1.000   0.1919   0.02789   0.01629  -0.0530   0.6826   0.3619
  -0.750   0.2221   0.02753   0.01591  -0.0528   0.6758   0.3818
  -0.500   0.2441   0.02755   0.01603  -0.0520   0.6657   0.4029
  -0.250   0.2719   0.02717   0.01576  -0.0514   0.6587   0.4292
   0.000   0.2928   0.02708   0.01589  -0.0503   0.6493   0.4628
   0.250   0.3164   0.02646   0.01569  -0.0491   0.6420   0.5342
   0.750   0.4963   0.02557   0.01524  -0.0707   0.6230   1.0000
   1.000   0.5156   0.02599   0.01555  -0.0694   0.6129   1.0000
   1.250   0.5393   0.02606   0.01544  -0.0681   0.6055   1.0000
   1.500   0.5577   0.02653   0.01583  -0.0667   0.5953   1.0000
   1.750   0.5815   0.02659   0.01573  -0.0654   0.5880   1.0000
   2.000   0.5992   0.02710   0.01619  -0.0639   0.5777   1.0000
   2.250   0.6231   0.02714   0.01609  -0.0626   0.5706   1.0000
   2.500   0.6399   0.02771   0.01664  -0.0610   0.5602   1.0000
   2.750   0.6640   0.02775   0.01656  -0.0598   0.5532   1.0000
   3.000   0.6798   0.02839   0.01719  -0.0581   0.5428   1.0000
   3.250   0.7040   0.02843   0.01712  -0.0568   0.5360   1.0000
   3.500   0.7187   0.02916   0.01787  -0.0551   0.5258   1.0000
   3.750   0.7424   0.02927   0.01788  -0.0538   0.5192   1.0000
   4.000   0.7564   0.03005   0.01868  -0.0520   0.5096   1.0000
   4.250   0.7788   0.03024   0.01881  -0.0507   0.5028   1.0000
   4.500   0.7933   0.03100   0.01958  -0.0489   0.4941   1.0000
   4.750   0.8127   0.03143   0.01997  -0.0474   0.4870   1.0000
   5.000   0.8324   0.03188   0.02039  -0.0459   0.4806   1.0000
   5.250   0.8436   0.03284   0.02141  -0.0439   0.4721   1.0000
   5.500   0.8701   0.03283   0.02133  -0.0430   0.4671   1.0000
   5.750   0.8729   0.03434   0.02293  -0.0402   0.4580   1.0000
   6.000   0.8946   0.03465   0.02322  -0.0390   0.4523   1.0000
   6.250   0.9063   0.03562   0.02422  -0.0370   0.4457   1.0000
   6.500   0.9142   0.03677   0.02543  -0.0347   0.4384   1.0000
   6.750   0.9435   0.03662   0.02523  -0.0340   0.4339   1.0000
   7.000   0.9327   0.03890   0.02763  -0.0303   0.4250   1.0000
   7.250   0.9551   0.03907   0.02781  -0.0291   0.4193   1.0000
   7.500   0.9575   0.04039   0.02917  -0.0263   0.4115   1.0000
   7.750   0.9722   0.04077   0.02955  -0.0243   0.4036   1.0000
   8.000   0.9796   0.04160   0.03039  -0.0218   0.3954   1.0000
   8.250   0.9917   0.04196   0.03075  -0.0195   0.3870   1.0000
   8.500   0.9923   0.04307   0.03188  -0.0165   0.3788   1.0000
   8.750   1.0005   0.04379   0.03261  -0.0142   0.3706   1.0000
   9.000   1.0086   0.04473   0.03355  -0.0122   0.3633   1.0000
   9.250   0.9967   0.04734   0.03623  -0.0099   0.3549   1.0000
   9.500   1.0503   0.04499   0.03385  -0.0095   0.3502   1.0000
   9.750   0.9894   0.05197   0.04099  -0.0068   0.3390   1.0000
  10.000   1.0371   0.04956   0.03856  -0.0056   0.3345   1.0000
  10.250   0.9818   0.05719   0.04632  -0.0047   0.3223   1.0000
  10.500   1.0250   0.05485   0.04399  -0.0031   0.3181   1.0000
  10.750   0.9718   0.06320   0.05245  -0.0034   0.3050   1.0000
  11.000   1.0096   0.06123   0.05052  -0.0016   0.3013   1.0000
  11.250   0.9581   0.07024   0.05961  -0.0029   0.2873   1.0000
  11.500   0.9957   0.06800   0.05742  -0.0009   0.2841   1.0000
  12.000   0.9128   0.08555   0.07507  -0.0049   0.2568   1.0000
  12.250   0.9344   0.08522   0.07479  -0.0035   0.2527   1.0000
  12.500   0.9674   0.08318   0.07280  -0.0015   0.2505   1.0000
  13.000   0.8751   0.10541   0.09509  -0.0090   0.2259   1.0000
  13.250   0.8836   0.10763   0.09736  -0.0089   0.2222   1.0000
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