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GOE 81 AIRFOIL (goe81-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 81 AIRFOIL (goe81-il)
Reynolds number: 1,000,000
Max Cl/Cd: 104.82 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe81-il-1000000-n5.txt
Download as CSV file: xf-goe81-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 81 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2373   0.10213   0.10012  -0.0407   0.8820   0.0076
  -9.250  -0.2299   0.09916   0.09711  -0.0420   0.8730   0.0079
  -9.000  -0.2276   0.09450   0.09242  -0.0442   0.8639   0.0088
  -8.750  -0.2174   0.09234   0.09024  -0.0454   0.8545   0.0089
  -8.500  -0.2074   0.09008   0.08793  -0.0467   0.8438   0.0091
  -8.250  -0.1974   0.08767   0.08550  -0.0481   0.8327   0.0092
  -8.000  -0.1877   0.08510   0.08289  -0.0498   0.8215   0.0095
  -7.750  -0.1783   0.08242   0.08018  -0.0517   0.8091   0.0097
  -7.500  -0.1665   0.07938   0.07708  -0.0546   0.7950   0.0101
  -7.250  -0.1532   0.07440   0.07204  -0.0604   0.7805   0.0111
  -7.000  -0.1355   0.07225   0.06982  -0.0631   0.7641   0.0112
  -6.750  -0.1167   0.06982   0.06731  -0.0664   0.7482   0.0115
  -6.500  -0.0967   0.06703   0.06445  -0.0702   0.7339   0.0117
  -6.250  -0.0749   0.06395   0.06130  -0.0745   0.7209   0.0121
  -6.000  -0.0463   0.05790   0.05514  -0.0834   0.7091   0.0135
  -5.750  -0.0233   0.05598   0.05315  -0.0860   0.6964   0.0137
  -5.500   0.0014   0.05381   0.05091  -0.0891   0.6855   0.0139
  -5.250   0.0282   0.05124   0.04826  -0.0928   0.6766   0.0142
  -5.000   0.0567   0.04840   0.04534  -0.0968   0.6695   0.0146
  -4.750   0.0988   0.04238   0.03914  -0.1054   0.6624   0.0162
  -4.500   0.1240   0.04066   0.03734  -0.1071   0.6544   0.0164
  -4.250   0.1513   0.03889   0.03551  -0.1091   0.6474   0.0166
  -4.000   0.1801   0.03694   0.03346  -0.1113   0.6410   0.0169
  -3.750   0.2106   0.03469   0.03111  -0.1138   0.6355   0.0172
  -3.500   0.2419   0.03231   0.02861  -0.1162   0.6295   0.0175
  -3.250   0.2735   0.02996   0.02611  -0.1183   0.6235   0.0181
  -3.000   0.3143   0.02554   0.02139  -0.1213   0.6182   0.0193
  -2.750   0.3442   0.02305   0.01871  -0.1228   0.6106   0.0195
  -2.500   0.3733   0.02147   0.01699  -0.1237   0.6020   0.0196
  -2.250   0.4013   0.02043   0.01581  -0.1242   0.5922   0.0198
  -2.000   0.4294   0.01962   0.01492  -0.1248   0.5844   0.0202
  -1.750   0.4593   0.01808   0.01320  -0.1253   0.5773   0.0204
  -1.500   0.4900   0.01629   0.01120  -0.1259   0.5705   0.0205
  -1.250   0.5196   0.01494   0.00963  -0.1262   0.5617   0.0209
  -1.000   0.5492   0.01370   0.00817  -0.1265   0.5512   0.0213
  -0.750   0.5781   0.01263   0.00686  -0.1266   0.5374   0.0215
  -0.500   0.6064   0.01183   0.00580  -0.1266   0.5156   0.0217
  -0.250   0.6334   0.01136   0.00504  -0.1264   0.4805   0.0220
   0.000   0.6601   0.01098   0.00438  -0.1262   0.4481   0.0221
   0.250   0.6871   0.01068   0.00388  -0.1260   0.4261   0.0222
   0.500   0.7145   0.01046   0.00353  -0.1259   0.4123   0.0226
   0.750   0.7419   0.01035   0.00332  -0.1258   0.4024   0.0228
   1.000   0.7695   0.01011   0.00302  -0.1258   0.3938   0.0232
   1.250   0.7970   0.00995   0.00283  -0.1258   0.3859   0.0236
   1.500   0.8244   0.00989   0.00274  -0.1257   0.3773   0.0239
   1.750   0.8519   0.00985   0.00268  -0.1257   0.3694   0.0242
   2.000   0.8789   0.00988   0.00265  -0.1256   0.3562   0.0245
   2.250   0.9056   0.00996   0.00265  -0.1254   0.3386   0.0250
   2.500   0.9326   0.01003   0.00267  -0.1253   0.3272   0.0257
   2.750   0.9594   0.01010   0.00268  -0.1251   0.3127   0.0260
   3.000   0.9856   0.01024   0.00273  -0.1249   0.2930   0.0264
   3.250   1.0115   0.01044   0.00283  -0.1247   0.2717   0.0269
   3.500   1.0371   0.01067   0.00296  -0.1244   0.2520   0.0274
   3.750   1.0626   0.01089   0.00309  -0.1240   0.2321   0.0281
   4.000   1.0880   0.01114   0.00325  -0.1237   0.2126   0.0291
   4.250   1.1127   0.01146   0.00347  -0.1233   0.1915   0.0300
   4.750   1.1585   0.01248   0.00414  -0.1218   0.1254   0.0329
   5.000   1.1840   0.01269   0.00433  -0.1215   0.1193   0.0353
   5.250   1.2103   0.01272   0.00462  -0.1214   0.1166   0.2344
   5.500   1.2325   0.01176   0.00499  -0.1208   0.1142   1.0000
   5.750   1.2578   0.01200   0.00522  -0.1204   0.1116   1.0000
   6.000   1.2827   0.01227   0.00546  -0.1200   0.1071   1.0000
   6.250   1.3080   0.01250   0.00568  -0.1197   0.1038   1.0000
   6.500   1.3328   0.01276   0.00593  -0.1193   0.0990   1.0000
   6.750   1.3564   0.01312   0.00624  -0.1187   0.0919   1.0000
   7.000   1.3779   0.01366   0.00663  -0.1178   0.0676   1.0000
   7.250   1.3994   0.01419   0.00708  -0.1169   0.0557   1.0000
   7.500   1.4222   0.01457   0.00746  -0.1163   0.0522   1.0000
   7.750   1.4451   0.01493   0.00782  -0.1156   0.0484   1.0000
   8.000   1.4682   0.01524   0.00815  -0.1149   0.0468   1.0000
   8.250   1.4902   0.01563   0.00855  -0.1142   0.0436   1.0000
   8.500   1.5107   0.01612   0.00903  -0.1131   0.0389   1.0000
   8.750   1.5276   0.01687   0.00967  -0.1116   0.0215   1.0000
   9.000   1.5436   0.01765   0.01042  -0.1099   0.0139   1.0000
   9.250   1.5625   0.01816   0.01096  -0.1086   0.0122   1.0000
   9.500   1.5804   0.01867   0.01151  -0.1072   0.0112   1.0000
   9.750   1.5959   0.01924   0.01212  -0.1053   0.0103   1.0000
  10.000   1.6091   0.01988   0.01280  -0.1031   0.0094   1.0000
  10.250   1.6236   0.02047   0.01343  -0.1012   0.0090   1.0000
  10.500   1.6374   0.02111   0.01412  -0.0993   0.0086   1.0000
  10.750   1.6503   0.02183   0.01490  -0.0973   0.0081   1.0000
  11.000   1.6623   0.02265   0.01575  -0.0954   0.0077   1.0000
  11.250   1.6730   0.02358   0.01673  -0.0934   0.0072   1.0000
  11.500   1.6819   0.02471   0.01793  -0.0913   0.0067   1.0000
  11.750   1.6927   0.02572   0.01901  -0.0896   0.0066   1.0000
  12.000   1.7030   0.02684   0.02019  -0.0880   0.0064   1.0000
  12.250   1.7123   0.02806   0.02147  -0.0864   0.0062   1.0000
  12.500   1.7208   0.02938   0.02287  -0.0849   0.0059   1.0000
  12.750   1.7285   0.03083   0.02439  -0.0834   0.0057   1.0000
  13.000   1.7351   0.03241   0.02604  -0.0819   0.0056   1.0000
  13.250   1.7408   0.03413   0.02783  -0.0806   0.0054   1.0000
  13.500   1.7454   0.03602   0.02979  -0.0793   0.0052   1.0000
  13.750   1.7483   0.03813   0.03198  -0.0781   0.0050   1.0000
  14.000   1.7489   0.04056   0.03449  -0.0769   0.0048   1.0000
  14.250   1.7473   0.04332   0.03735  -0.0759   0.0047   1.0000
  14.500   1.7493   0.04573   0.03985  -0.0751   0.0046   1.0000
  14.750   1.7500   0.04835   0.04257  -0.0745   0.0045   1.0000
  15.000   1.7496   0.05120   0.04552  -0.0739   0.0044   1.0000
  15.250   1.7481   0.05426   0.04868  -0.0736   0.0044   1.0000
  15.500   1.7453   0.05753   0.05204  -0.0733   0.0043   1.0000
  15.750   1.7416   0.06102   0.05563  -0.0732   0.0042   1.0000
  16.000   1.7364   0.06478   0.05951  -0.0732   0.0041   1.0000
  16.250   1.7303   0.06877   0.06359  -0.0734   0.0040   1.0000
  16.500   1.7233   0.07293   0.06786  -0.0737   0.0040   1.0000
  16.750   1.7151   0.07738   0.07243  -0.0743   0.0039   1.0000
  17.000   1.7063   0.08206   0.07722  -0.0750   0.0039   1.0000
  17.250   1.6965   0.08697   0.08224  -0.0760   0.0038   1.0000
  17.500   1.6858   0.09209   0.08747  -0.0771   0.0038   1.0000
  17.750   1.6742   0.09748   0.09298  -0.0785   0.0037   1.0000
  18.000   1.6622   0.10297   0.09858  -0.0800   0.0037   1.0000
  18.250   1.6506   0.10846   0.10417  -0.0816   0.0036   1.0000
  18.500   1.6377   0.11418   0.11000  -0.0834   0.0036   1.0000
  18.750   1.6246   0.12002   0.11595  -0.0854   0.0036   1.0000
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