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GOE 796 AIRFOIL (goe796-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 796 AIRFOIL (goe796-il)
Reynolds number: 500,000
Max Cl/Cd: 105.85 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe796-il-500000.txt
Download as CSV file: xf-goe796-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 796 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3084   0.10346   0.10127  -0.0445   1.0000   0.0407
 -10.500  -0.3138   0.09973   0.09756  -0.0448   0.9997   0.0407
 -10.250  -0.6917   0.03916   0.03614  -0.0796   0.9930   0.0260
 -10.000  -0.6959   0.03092   0.02709  -0.0830   0.9865   0.0254
  -9.750  -0.6751   0.02706   0.02275  -0.0851   0.9839   0.0252
  -9.500  -0.6504   0.02463   0.01999  -0.0864   0.9810   0.0252
  -9.250  -0.6245   0.02278   0.01789  -0.0873   0.9772   0.0253
  -9.000  -0.5940   0.02120   0.01608  -0.0888   0.9749   0.0254
  -8.750  -0.5617   0.01983   0.01452  -0.0904   0.9731   0.0255
  -8.500  -0.5290   0.01866   0.01318  -0.0920   0.9712   0.0257
  -8.250  -0.5032   0.01773   0.01213  -0.0919   0.9658   0.0259
  -8.000  -0.4744   0.01686   0.01113  -0.0924   0.9617   0.0261
  -7.750  -0.4443   0.01604   0.01020  -0.0931   0.9584   0.0263
  -7.500  -0.4201   0.01539   0.00946  -0.0924   0.9517   0.0265
  -7.250  -0.3937   0.01476   0.00874  -0.0922   0.9461   0.0267
  -7.000  -0.3681   0.01420   0.00809  -0.0917   0.9404   0.0270
  -6.750  -0.3436   0.01369   0.00751  -0.0909   0.9329   0.0272
  -6.500  -0.3178   0.01321   0.00695  -0.0904   0.9271   0.0275
  -6.250  -0.2932   0.01279   0.00647  -0.0896   0.9184   0.0278
  -6.000  -0.2677   0.01229   0.00589  -0.0890   0.9120   0.0287
  -5.750  -0.2422   0.01191   0.00549  -0.0884   0.9027   0.0299
  -5.500  -0.2158   0.01159   0.00512  -0.0880   0.8953   0.0313
  -5.250  -0.1894   0.01129   0.00477  -0.0875   0.8856   0.0332
  -5.000  -0.1628   0.01096   0.00445  -0.0871   0.8767   0.0382
  -4.750  -0.1360   0.01069   0.00416  -0.0868   0.8677   0.0475
  -4.500  -0.1090   0.01045   0.00391  -0.0865   0.8577   0.0558
  -4.250  -0.0816   0.01028   0.00368  -0.0863   0.8486   0.0621
  -4.000  -0.0542   0.01010   0.00350  -0.0861   0.8386   0.0688
  -3.750  -0.0267   0.00997   0.00337  -0.0860   0.8286   0.0767
  -3.500   0.0010   0.00987   0.00322  -0.0858   0.8190   0.0838
  -3.250   0.0287   0.00979   0.00313  -0.0857   0.8084   0.0927
  -3.000   0.0565   0.00970   0.00301  -0.0856   0.7988   0.1007
  -2.500   0.1122   0.00956   0.00280  -0.0855   0.7811   0.1169
  -2.250   0.1401   0.00950   0.00269  -0.0854   0.7732   0.1238
  -2.000   0.1681   0.00943   0.00260  -0.0854   0.7647   0.1298
  -1.750   0.1959   0.00935   0.00251  -0.0853   0.7570   0.1385
  -1.500   0.2238   0.00927   0.00244  -0.0853   0.7493   0.1488
  -1.250   0.2516   0.00920   0.00237  -0.0853   0.7421   0.1624
  -1.000   0.2794   0.00907   0.00232  -0.0853   0.7341   0.1818
  -0.750   0.3068   0.00894   0.00226  -0.0852   0.7270   0.2201
  -0.500   0.3339   0.00865   0.00225  -0.0852   0.7199   0.2978
  -0.250   0.3599   0.00826   0.00223  -0.0850   0.7138   0.4256
   0.000   0.3840   0.00767   0.00227  -0.0845   0.7078   0.6159
   0.250   0.4047   0.00711   0.00234  -0.0827   0.7017   0.8063
   0.500   0.4400   0.00700   0.00248  -0.0835   0.6963   0.9564
   0.750   0.4915   0.00707   0.00253  -0.0885   0.6888   0.9882
   1.000   0.5421   0.00716   0.00252  -0.0935   0.6803   0.9992
   1.250   0.5700   0.00719   0.00252  -0.0935   0.6717   1.0000
   1.500   0.5957   0.00726   0.00252  -0.0930   0.6646   1.0000
   1.750   0.6213   0.00730   0.00254  -0.0925   0.6567   1.0000
   2.000   0.6469   0.00738   0.00255  -0.0920   0.6497   1.0000
   2.250   0.6726   0.00742   0.00259  -0.0915   0.6411   1.0000
   2.500   0.6979   0.00750   0.00262  -0.0910   0.6323   1.0000
   2.750   0.7231   0.00757   0.00265  -0.0904   0.6214   1.0000
   3.000   0.7485   0.00764   0.00271  -0.0898   0.6109   1.0000
   3.250   0.7736   0.00774   0.00276  -0.0892   0.6005   1.0000
   3.500   0.7984   0.00785   0.00282  -0.0886   0.5882   1.0000
   3.750   0.8232   0.00796   0.00290  -0.0879   0.5739   1.0000
   4.000   0.8477   0.00809   0.00299  -0.0872   0.5580   1.0000
   4.250   0.8720   0.00825   0.00309  -0.0865   0.5394   1.0000
   4.500   0.8955   0.00846   0.00322  -0.0856   0.5153   1.0000
   4.750   0.9183   0.00872   0.00337  -0.0847   0.4883   1.0000
   5.000   0.9405   0.00905   0.00356  -0.0836   0.4594   1.0000
   5.250   0.9623   0.00941   0.00379  -0.0825   0.4316   1.0000
   5.500   0.9836   0.00983   0.00406  -0.0814   0.4043   1.0000
   5.750   1.0059   0.01019   0.00431  -0.0805   0.3822   1.0000
   6.000   1.0287   0.01052   0.00457  -0.0796   0.3659   1.0000
   6.250   1.0519   0.01083   0.00484  -0.0788   0.3528   1.0000
   6.500   1.0748   0.01115   0.00512  -0.0780   0.3406   1.0000
   6.750   1.0976   0.01147   0.00540  -0.0772   0.3276   1.0000
   7.000   1.1205   0.01178   0.00567  -0.0764   0.3133   1.0000
   7.250   1.1432   0.01210   0.00596  -0.0756   0.2987   1.0000
   7.500   1.1654   0.01243   0.00626  -0.0748   0.2829   1.0000
   7.750   1.1868   0.01280   0.00657  -0.0737   0.2633   1.0000
   8.000   1.2065   0.01327   0.00692  -0.0725   0.2351   1.0000
   8.250   1.2233   0.01391   0.00738  -0.0708   0.2016   1.0000
   8.500   1.2393   0.01456   0.00791  -0.0690   0.1813   1.0000
   8.750   1.2561   0.01514   0.00844  -0.0673   0.1685   1.0000
   9.000   1.2723   0.01566   0.00894  -0.0655   0.1587   1.0000
   9.250   1.2864   0.01627   0.00951  -0.0633   0.1490   1.0000
   9.500   1.3043   0.01670   0.00977  -0.0618   0.1406   1.0000
   9.750   1.3202   0.01726   0.01053  -0.0600   0.1319   1.0000
  10.000   1.3358   0.01786   0.01110  -0.0583   0.1211   1.0000
  10.250   1.3518   0.01845   0.01168  -0.0567   0.1099   1.0000
  10.500   1.3660   0.01915   0.01236  -0.0550   0.0989   1.0000
  10.750   1.3794   0.01993   0.01311  -0.0532   0.0895   1.0000
  11.000   1.3915   0.02080   0.01396  -0.0513   0.0814   1.0000
  11.250   1.4042   0.02166   0.01483  -0.0496   0.0745   1.0000
  11.500   1.4161   0.02260   0.01578  -0.0478   0.0677   1.0000
  11.750   1.4257   0.02372   0.01688  -0.0459   0.0601   1.0000
  12.000   1.4361   0.02481   0.01797  -0.0442   0.0520   1.0000
  12.250   1.4436   0.02615   0.01929  -0.0424   0.0425   1.0000
  12.500   1.4484   0.02774   0.02083  -0.0404   0.0336   1.0000
  12.750   1.4533   0.02939   0.02248  -0.0386   0.0283   1.0000
  13.000   1.4585   0.03109   0.02422  -0.0369   0.0251   1.0000
  13.250   1.4609   0.03308   0.02625  -0.0353   0.0228   1.0000
  13.500   1.4644   0.03504   0.02830  -0.0339   0.0213   1.0000
  13.750   1.4684   0.03702   0.03037  -0.0327   0.0201   1.0000
  14.000   1.4695   0.03933   0.03276  -0.0315   0.0191   1.0000
  14.250   1.4662   0.04214   0.03565  -0.0303   0.0182   1.0000
  14.500   1.4641   0.04495   0.03858  -0.0294   0.0175   1.0000
  14.750   1.4662   0.04739   0.04113  -0.0288   0.0169   1.0000
  15.000   1.4667   0.05008   0.04393  -0.0282   0.0163   1.0000
  15.250   1.4658   0.05301   0.04695  -0.0279   0.0157   1.0000
  15.500   1.4629   0.05626   0.05029  -0.0277   0.0152   1.0000
  15.750   1.4555   0.06014   0.05426  -0.0277   0.0147   1.0000
  16.000   1.4427   0.06484   0.05907  -0.0279   0.0143   1.0000
  16.250   1.4377   0.06871   0.06306  -0.0283   0.0139   1.0000
  16.500   1.4357   0.07227   0.06673  -0.0288   0.0135   1.0000
  16.750   1.4310   0.07627   0.07086  -0.0295   0.0131   1.0000
  17.000   1.4252   0.08052   0.07522  -0.0303   0.0128   1.0000
  17.250   1.4185   0.08502   0.07984  -0.0314   0.0125   1.0000
  17.500   1.4107   0.08975   0.08467  -0.0327   0.0122   1.0000
  17.750   1.4020   0.09467   0.08969  -0.0341   0.0119   1.0000
  18.000   1.3924   0.09983   0.09495  -0.0358   0.0117   1.0000
  18.250   1.3818   0.10519   0.10041  -0.0376   0.0115   1.0000
  18.500   1.3698   0.11078   0.10608  -0.0395   0.0113   1.0000
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