Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

GOE 478 AIRFOIL (goe478-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 478 AIRFOIL (goe478-il)
Reynolds number: 100,000
Max Cl/Cd: 53 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe478-il-100000-n5.txt
Download as CSV file: xf-goe478-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 478 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.2844   0.13024   0.12459  -0.0439   1.0000   0.0787
 -11.250  -0.2975   0.12810   0.12252  -0.0457   1.0000   0.0793
 -11.000  -0.2995   0.12531   0.11981  -0.0458   1.0000   0.0796
 -10.750  -0.2864   0.12239   0.11692  -0.0437   1.0000   0.0803
 -10.500  -0.2833   0.12015   0.11474  -0.0425   1.0000   0.0809
 -10.250  -0.2841   0.11817   0.11283  -0.0411   1.0000   0.0816
 -10.000  -0.2893   0.11654   0.11128  -0.0393   1.0000   0.0821
  -9.500  -0.2862   0.10374   0.09843  -0.0513   0.9887   0.0640
  -9.250  -0.2645   0.10068   0.09535  -0.0529   0.9842   0.0615
  -8.750  -0.2661   0.08720   0.08183  -0.0666   0.9669   0.0567
  -8.500  -0.2554   0.08306   0.07770  -0.0706   0.9595   0.0565
  -8.250  -0.2456   0.07922   0.07385  -0.0740   0.9513   0.0561
  -8.000  -0.2364   0.07456   0.06918  -0.0792   0.9439   0.0555
  -7.750  -0.2368   0.06937   0.06397  -0.0846   0.9326   0.0549
  -7.500  -0.2348   0.06172   0.05618  -0.0931   0.9241   0.0541
  -7.250  -0.2434   0.05338   0.04755  -0.0989   0.9131   0.0533
  -7.000  -0.2542   0.04552   0.03918  -0.1014   0.9031   0.0529
  -6.750  -0.2472   0.04102   0.03423  -0.1022   0.8959   0.0535
  -6.500  -0.2291   0.03704   0.02971  -0.1037   0.8916   0.0546
  -6.250  -0.2230   0.03454   0.02677  -0.1014   0.8814   0.0553
  -6.000  -0.2009   0.03178   0.02346  -0.1016   0.8761   0.0560
  -5.750  -0.1772   0.02965   0.02083  -0.1016   0.8711   0.0566
  -5.500  -0.1594   0.02852   0.01955  -0.1000   0.8632   0.0572
  -5.250  -0.1308   0.02736   0.01827  -0.1004   0.8584   0.0581
  -5.000  -0.0981   0.02619   0.01695  -0.1014   0.8547   0.0593
  -4.750  -0.0813   0.02553   0.01615  -0.0994   0.8461   0.0608
  -4.500  -0.0529   0.02453   0.01492  -0.0994   0.8405   0.0629
  -4.250  -0.0202   0.02360   0.01390  -0.1002   0.8366   0.0647
  -4.000  -0.0011   0.02315   0.01345  -0.0986   0.8295   0.0662
  -3.750   0.0247   0.02253   0.01275  -0.0981   0.8239   0.0681
  -3.500   0.0556   0.02179   0.01189  -0.0984   0.8197   0.0707
  -3.250   0.0805   0.02137   0.01151  -0.0978   0.8141   0.0735
  -3.000   0.1031   0.02104   0.01116  -0.0966   0.8073   0.0774
  -2.750   0.1327   0.02055   0.01067  -0.0967   0.8023   0.0822
  -2.500   0.1610   0.02012   0.01018  -0.0965   0.7972   0.0883
  -2.250   0.1816   0.01986   0.00998  -0.0950   0.7895   0.0955
  -2.000   0.2108   0.01940   0.00953  -0.0950   0.7840   0.1080
  -1.750   0.2370   0.01902   0.00919  -0.0944   0.7779   0.1243
  -1.500   0.2590   0.01878   0.00910  -0.0932   0.7701   0.1428
  -1.250   0.2902   0.01850   0.00886  -0.0935   0.7644   0.1687
  -1.000   0.3127   0.01839   0.00881  -0.0923   0.7562   0.1913
  -0.750   0.3393   0.01819   0.00862  -0.0917   0.7487   0.2180
  -0.500   0.3692   0.01783   0.00838  -0.0919   0.7425   0.2535
  -0.250   0.3890   0.01761   0.00836  -0.0903   0.7328   0.2902
   0.000   0.4200   0.01707   0.00811  -0.0907   0.7260   0.3677
   0.250   0.4356   0.01642   0.00823  -0.0881   0.7158   0.5721
   0.500   0.5270   0.01564   0.00820  -0.0991   0.7085   0.9470
   0.750   0.5856   0.01569   0.00812  -0.1052   0.6983   0.9981
   1.000   0.6112   0.01571   0.00800  -0.1045   0.6886   1.0000
   1.250   0.6281   0.01585   0.00806  -0.1022   0.6764   1.0000
   1.500   0.6509   0.01589   0.00797  -0.1010   0.6663   1.0000
   1.750   0.6689   0.01602   0.00803  -0.0989   0.6538   1.0000
   2.000   0.6878   0.01614   0.00809  -0.0970   0.6415   1.0000
   2.250   0.7093   0.01622   0.00807  -0.0955   0.6302   1.0000
   2.500   0.7298   0.01633   0.00810  -0.0939   0.6183   1.0000
   2.750   0.7498   0.01648   0.00819  -0.0922   0.6065   1.0000
   3.000   0.7723   0.01659   0.00820  -0.0909   0.5961   1.0000
   3.250   0.7947   0.01672   0.00823  -0.0896   0.5858   1.0000
   3.500   0.8166   0.01689   0.00833  -0.0883   0.5756   1.0000
   3.750   0.8414   0.01702   0.00832  -0.0874   0.5668   1.0000
   4.000   0.8622   0.01725   0.00850  -0.0860   0.5561   1.0000
   4.250   0.8854   0.01746   0.00859  -0.0849   0.5458   1.0000
   4.500   0.9077   0.01770   0.00872  -0.0836   0.5345   1.0000
   4.750   0.9285   0.01799   0.00896  -0.0822   0.5235   1.0000
   5.250   0.9721   0.01861   0.00945  -0.0797   0.5037   1.0000
   5.500   0.9969   0.01892   0.00965  -0.0790   0.4948   1.0000
   5.750   1.0144   0.01928   0.01006  -0.0771   0.4849   1.0000
   6.000   1.0382   0.01961   0.01030  -0.0762   0.4759   1.0000
   6.250   1.0544   0.01998   0.01073  -0.0741   0.4657   1.0000
   6.500   1.0764   0.02031   0.01101  -0.0730   0.4567   1.0000
   6.750   1.0917   0.02068   0.01146  -0.0708   0.4464   1.0000
   7.000   1.1111   0.02102   0.01176  -0.0692   0.4370   1.0000
   7.250   1.1257   0.02140   0.01222  -0.0669   0.4264   1.0000
   7.500   1.1423   0.02176   0.01259  -0.0649   0.4166   1.0000
   7.750   1.1562   0.02214   0.01299  -0.0624   0.4055   1.0000
   8.000   1.1675   0.02254   0.01344  -0.0596   0.3942   1.0000
   8.250   1.1775   0.02294   0.01385  -0.0565   0.3818   1.0000
   8.500   1.1854   0.02340   0.01428  -0.0532   0.3677   1.0000
   8.750   1.1915   0.02395   0.01484  -0.0498   0.3518   1.0000
   9.000   1.1974   0.02458   0.01545  -0.0466   0.3348   1.0000
   9.250   1.2030   0.02532   0.01616  -0.0435   0.3164   1.0000
   9.500   1.2082   0.02617   0.01698  -0.0405   0.2977   1.0000
   9.750   1.2133   0.02712   0.01787  -0.0378   0.2804   1.0000
  10.000   1.2177   0.02821   0.01889  -0.0351   0.2642   1.0000
  10.250   1.2216   0.02941   0.02003  -0.0326   0.2491   1.0000
  10.500   1.2250   0.03072   0.02128  -0.0302   0.2356   1.0000
  10.750   1.2289   0.03210   0.02264  -0.0280   0.2232   1.0000
  11.000   1.2331   0.03353   0.02406  -0.0261   0.2116   1.0000
  11.250   1.2364   0.03510   0.02560  -0.0242   0.2012   1.0000
  11.500   1.2395   0.03673   0.02722  -0.0224   0.1916   1.0000
  11.750   1.2438   0.03835   0.02888  -0.0209   0.1825   1.0000
  12.000   1.2454   0.04021   0.03072  -0.0193   0.1746   1.0000
  12.250   1.2501   0.04193   0.03251  -0.0180   0.1663   1.0000
  12.500   1.2508   0.04397   0.03451  -0.0167   0.1594   1.0000
  12.750   1.2552   0.04582   0.03646  -0.0156   0.1521   1.0000
  13.000   1.2562   0.04797   0.03860  -0.0145   0.1461   1.0000
  13.250   1.2601   0.04997   0.04068  -0.0137   0.1400   1.0000
  13.500   1.2618   0.05220   0.04296  -0.0128   0.1345   1.0000
  13.750   1.2642   0.05442   0.04519  -0.0121   0.1298   1.0000
  14.000   1.2675   0.05665   0.04751  -0.0115   0.1245   1.0000
  14.250   1.2694   0.05904   0.04991  -0.0110   0.1205   1.0000
  14.500   1.2725   0.06134   0.05225  -0.0106   0.1165   1.0000
  14.750   1.2761   0.06369   0.05471  -0.0103   0.1125   1.0000
  15.000   1.2793   0.06609   0.05715  -0.0100   0.1092   1.0000
  15.250   1.2838   0.06830   0.05931  -0.0097   0.1065   1.0000
  15.500   1.2881   0.07074   0.06191  -0.0096   0.1035   1.0000
  15.750   1.2917   0.07324   0.06451  -0.0096   0.1007   1.0000
  16.000   1.2952   0.07576   0.06711  -0.0096   0.0982   1.0000
  16.250   1.3001   0.07807   0.06942  -0.0096   0.0961   1.0000
  16.500   1.3048   0.08052   0.07194  -0.0096   0.0940   1.0000
  16.750   1.3066   0.08344   0.07504  -0.0100   0.0920   1.0000
  17.000   1.3086   0.08634   0.07806  -0.0104   0.0901   1.0000
  17.250   1.3110   0.08919   0.08101  -0.0108   0.0883   1.0000
  17.500   1.3146   0.09181   0.08369  -0.0112   0.0867   1.0000
  17.750   1.3225   0.09376   0.08563  -0.0113   0.0852   1.0000
  18.000   1.3181   0.09778   0.08985  -0.0125   0.0838   1.0000
  18.250   1.3112   0.10226   0.09455  -0.0140   0.0823   1.0000
  18.500   1.3045   0.10676   0.09924  -0.0156   0.0810   1.0000
<< Back to GOE 478 AIRFOIL (goe478-il)

Polar data table (+)

Polar graphs


<< Back to GOE 478 AIRFOIL (goe478-il)