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GOE 101 AIRFOIL (goe101-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 101 AIRFOIL (goe101-il)
Reynolds number: 200,000
Max Cl/Cd: 77.93 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe101-il-200000.txt
Download as CSV file: xf-goe101-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 101 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3745   0.09743   0.09393  -0.0170   1.0000   0.0278
  -8.000  -0.3730   0.09521   0.09177  -0.0192   1.0000   0.0282
  -7.750  -0.3747   0.09324   0.08987  -0.0215   1.0000   0.0284
  -7.500  -0.3694   0.09045   0.08712  -0.0253   1.0000   0.0286
  -7.250  -0.3602   0.08738   0.08407  -0.0303   1.0000   0.0287
  -7.000  -0.3499   0.08394   0.08063  -0.0334   1.0000   0.0288
  -6.750  -0.3520   0.07786   0.07463  -0.0312   1.0000   0.0295
  -6.500  -0.3469   0.07454   0.07134  -0.0293   1.0000   0.0302
  -6.250  -0.3394   0.07145   0.06827  -0.0296   1.0000   0.0308
  -6.000  -0.3308   0.06837   0.06521  -0.0305   1.0000   0.0316
  -5.750  -0.3212   0.06524   0.06207  -0.0318   1.0000   0.0325
  -5.500  -0.3106   0.06213   0.05895  -0.0333   1.0000   0.0335
  -5.250  -0.2991   0.05894   0.05574  -0.0348   1.0000   0.0349
  -5.000  -0.2851   0.05575   0.05249  -0.0366   1.0000   0.0366
  -4.750  -0.2543   0.05334   0.04973  -0.0411   1.0000   0.0391
  -4.500  -0.2372   0.04864   0.04483  -0.0430   0.9990   0.0398
  -4.250  -0.2114   0.04381   0.04016  -0.0465   0.9939   0.0426
  -4.000  -0.1686   0.04029   0.03643  -0.0518   0.9871   0.0489
  -3.750  -0.0775   0.01849   0.01457  -0.0636   0.9641   0.0588
  -3.500  -0.0366   0.01497   0.01064  -0.0678   0.9569   0.0683
  -3.250  -0.0023   0.01260   0.00800  -0.0702   0.9454   0.0818
  -3.000  -0.0007   0.02695   0.02199  -0.0691   0.9579   0.0842
  -2.750   0.0370   0.02470   0.01951  -0.0717   0.9474   0.0984
  -2.500   0.0745   0.02317   0.01761  -0.0739   0.9353   0.1234
  -2.250   0.1069   0.02132   0.01578  -0.0754   0.9201   0.1464
  -1.500   0.2118   0.01528   0.00814  -0.0739   0.8617   0.0705
  -1.250   0.2399   0.01444   0.00696  -0.0729   0.8373   0.0674
  -1.000   0.2667   0.01418   0.00646  -0.0718   0.8113   0.0655
  -0.750   0.2924   0.01338   0.00549  -0.0708   0.7855   0.0651
  -0.500   0.3179   0.01286   0.00483  -0.0699   0.7598   0.0653
  -0.250   0.3430   0.01233   0.00419  -0.0690   0.7362   0.0661
   0.000   0.3680   0.01193   0.00374  -0.0682   0.7148   0.0705
   0.250   0.3936   0.01175   0.00347  -0.0676   0.6943   0.0732
   0.500   0.4195   0.01164   0.00325  -0.0670   0.6755   0.0758
   0.750   0.4457   0.01159   0.00305  -0.0664   0.6589   0.0804
   1.000   0.4720   0.01146   0.00291  -0.0659   0.6441   0.1029
   1.250   0.5065   0.00942   0.00289  -0.0674   0.6305   1.0000
   1.500   0.5328   0.00961   0.00292  -0.0669   0.6178   1.0000
   1.750   0.5591   0.00981   0.00299  -0.0665   0.6059   1.0000
   2.000   0.5854   0.01001   0.00307  -0.0661   0.5948   1.0000
   2.250   0.6117   0.01023   0.00316  -0.0657   0.5841   1.0000
   2.500   0.6379   0.01041   0.00327  -0.0653   0.5730   1.0000
   2.750   0.6641   0.01059   0.00342  -0.0649   0.5615   1.0000
   3.000   0.6901   0.01078   0.00355  -0.0645   0.5497   1.0000
   3.250   0.7161   0.01097   0.00368  -0.0641   0.5383   1.0000
   3.500   0.7423   0.01119   0.00383  -0.0637   0.5288   1.0000
   3.750   0.7687   0.01138   0.00409  -0.0634   0.5201   1.0000
   4.000   0.7950   0.01162   0.00431  -0.0631   0.5123   1.0000
   4.250   0.8212   0.01181   0.00454  -0.0627   0.5030   1.0000
   4.500   0.8471   0.01200   0.00477  -0.0623   0.4924   1.0000
   4.750   0.8729   0.01220   0.00502  -0.0618   0.4820   1.0000
   5.000   0.8989   0.01242   0.00527  -0.0614   0.4727   1.0000
   5.250   0.9246   0.01261   0.00556  -0.0610   0.4621   1.0000
   5.500   0.9492   0.01273   0.00571  -0.0603   0.4450   1.0000
   5.750   0.9732   0.01280   0.00586  -0.0595   0.4210   1.0000
   6.000   0.9974   0.01296   0.00605  -0.0588   0.3998   1.0000
   6.250   1.0209   0.01310   0.00622  -0.0580   0.3634   1.0000
   6.500   1.0434   0.01343   0.00646  -0.0571   0.3087   1.0000
   6.750   1.0593   0.01464   0.00710  -0.0556   0.2101   1.0000
   7.000   1.0692   0.01688   0.00847  -0.0536   0.0824   1.0000
   7.250   1.0840   0.01858   0.00982  -0.0518   0.0399   1.0000
   7.500   1.1031   0.01964   0.01104  -0.0504   0.0348   1.0000
   7.750   1.1187   0.02104   0.01255  -0.0487   0.0315   1.0000
   8.000   1.1325   0.02255   0.01419  -0.0467   0.0293   1.0000
   8.250   1.1481   0.02382   0.01559  -0.0451   0.0276   1.0000
   8.500   1.1622   0.02534   0.01722  -0.0431   0.0264   1.0000
   8.750   1.1767   0.02698   0.01898  -0.0413   0.0256   1.0000
   9.000   1.1924   0.02881   0.02091  -0.0396   0.0250   1.0000
   9.250   1.2101   0.03086   0.02309  -0.0382   0.0247   1.0000
   9.500   1.2287   0.03311   0.02550  -0.0370   0.0243   1.0000
   9.750   1.2452   0.03550   0.02800  -0.0359   0.0230   1.0000
  10.000   1.2614   0.03883   0.03152  -0.0349   0.0223   1.0000
  10.250   1.2751   0.04150   0.03451  -0.0333   0.0225   1.0000
  10.500   1.2843   0.04435   0.03781  -0.0312   0.0232   1.0000
  10.750   1.2805   0.04909   0.04323  -0.0278   0.0253   1.0000
  11.000   1.2709   0.05373   0.04830  -0.0248   0.0270   1.0000
  11.250   1.2570   0.05808   0.05293  -0.0219   0.0282   1.0000
  11.500   1.1586   0.05356   0.04886  -0.0155   0.0271   1.0000
  11.750   1.1370   0.05884   0.05437  -0.0153   0.0276   1.0000
  12.000   1.1143   0.06458   0.06031  -0.0159   0.0279   1.0000
  12.250   1.0902   0.07085   0.06678  -0.0174   0.0281   1.0000
  12.500   1.0659   0.07749   0.07358  -0.0197   0.0282   1.0000
  12.750   1.0409   0.08452   0.08078  -0.0228   0.0283   1.0000
  13.000   1.0147   0.09190   0.08833  -0.0266   0.0284   1.0000
  13.250   0.9874   0.09960   0.09618  -0.0312   0.0283   1.0000
  13.500   0.9589   0.10767   0.10441  -0.0364   0.0283   1.0000
  13.750   0.9247   0.11612   0.11300  -0.0426   0.0282   1.0000
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