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GOE 81 AIRFOIL (goe81-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 81 AIRFOIL (goe81-il)
Reynolds number: 500,000
Max Cl/Cd: 102.53 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe81-il-500000-n5.txt
Download as CSV file: xf-goe81-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.1692   0.08833   0.08580  -0.0509   0.8862   0.0147
  -7.750  -0.1605   0.08551   0.08293  -0.0525   0.8752   0.0147
  -7.500  -0.1515   0.08273   0.08012  -0.0543   0.8643   0.0149
  -7.250  -0.1384   0.07889   0.07624  -0.0594   0.8536   0.0163
  -7.000  -0.1248   0.07676   0.07407  -0.0606   0.8431   0.0167
  -6.750  -0.1087   0.07416   0.07144  -0.0634   0.8315   0.0173
  -6.500  -0.0888   0.07102   0.06824  -0.0680   0.8201   0.0189
  -6.250  -0.0662   0.06737   0.06451  -0.0737   0.8081   0.0191
  -6.000  -0.0070   0.04612   0.04321  -0.0784   0.7585   0.0193
  -5.750   0.0055   0.04346   0.04049  -0.0782   0.7466   0.0195
  -5.500   0.0224   0.04080   0.03777  -0.0800   0.7353   0.0199
  -5.250   0.0425   0.03798   0.03489  -0.0829   0.7251   0.0205
  -5.000   0.0651   0.03500   0.03182  -0.0864   0.7159   0.0215
  -4.750   0.1044   0.03074   0.02736  -0.0954   0.7065   0.0228
  -4.500   0.1335   0.02726   0.02373  -0.0997   0.6979   0.0229
  -4.250   0.1621   0.02412   0.02043  -0.1031   0.6899   0.0229
  -4.000   0.1859   0.02107   0.01729  -0.1053   0.6831   0.0231
  -3.750   0.2063   0.01925   0.01541  -0.1060   0.6748   0.0234
  -3.500   0.2297   0.01769   0.01378  -0.1071   0.6672   0.0239
  -3.250   0.2564   0.01606   0.01204  -0.1088   0.6600   0.0249
  -3.000   0.2934   0.01415   0.00988  -0.1116   0.6549   0.0272
  -2.750   0.3260   0.01229   0.00781  -0.1136   0.6501   0.0274
  -2.500   0.3556   0.01073   0.00606  -0.1149   0.6447   0.0275
  -2.000   0.4281   0.02207   0.01672  -0.1235   0.6434   0.0278
  -1.750   0.4559   0.02054   0.01506  -0.1243   0.6364   0.0281
  -1.500   0.4841   0.01931   0.01368  -0.1248   0.6276   0.0284
  -1.250   0.5143   0.01792   0.01204  -0.1250   0.6191   0.0271
  -1.000   0.5428   0.01667   0.01060  -0.1254   0.6099   0.0267
  -0.750   0.5720   0.01553   0.00925  -0.1256   0.6016   0.0265
  -0.500   0.6010   0.01464   0.00811  -0.1256   0.5928   0.0270
  -0.250   0.6297   0.01389   0.00718  -0.1257   0.5836   0.0271
   0.000   0.6579   0.01314   0.00625  -0.1258   0.5739   0.0268
   0.250   0.6860   0.01253   0.00550  -0.1257   0.5628   0.0266
   0.500   0.7139   0.01206   0.00488  -0.1257   0.5492   0.0267
   0.750   0.7412   0.01173   0.00439  -0.1255   0.5314   0.0269
   1.000   0.7679   0.01155   0.00404  -0.1252   0.5055   0.0272
   1.250   0.7937   0.01155   0.00384  -0.1248   0.4747   0.0275
   1.500   0.8195   0.01139   0.00353  -0.1244   0.4514   0.0278
   1.750   0.8458   0.01128   0.00334  -0.1242   0.4354   0.0284
   2.000   0.8723   0.01127   0.00330  -0.1240   0.4232   0.0295
   2.250   0.8990   0.01126   0.00326  -0.1239   0.4129   0.0302
   2.500   0.9255   0.01128   0.00323  -0.1237   0.4015   0.0304
   2.750   0.9519   0.01135   0.00324  -0.1234   0.3891   0.0308
   3.000   0.9784   0.01141   0.00327  -0.1233   0.3765   0.0313
   3.250   1.0050   0.01149   0.00332  -0.1231   0.3651   0.0321
   3.500   1.0314   0.01159   0.00340  -0.1229   0.3563   0.0329
   3.750   1.0578   0.01171   0.00349  -0.1227   0.3454   0.0336
   4.000   1.0840   0.01184   0.00358  -0.1224   0.3332   0.0365
   4.250   1.1097   0.01203   0.00372  -0.1221   0.3190   0.0387
   4.500   1.1353   0.01224   0.00387  -0.1218   0.3048   0.0409
   4.750   1.1610   0.01231   0.00416  -0.1217   0.2894   0.2307
   5.250   1.2058   0.01176   0.00474  -0.1200   0.2554   1.0000
   5.500   1.2299   0.01213   0.00501  -0.1195   0.2389   1.0000
   5.750   1.2533   0.01255   0.00532  -0.1189   0.2206   1.0000
   6.000   1.2763   0.01300   0.00568  -0.1182   0.1998   1.0000
   6.250   1.2980   0.01356   0.00609  -0.1174   0.1734   1.0000
   6.500   1.3180   0.01427   0.00660  -0.1163   0.1423   1.0000
   6.750   1.3397   0.01479   0.00705  -0.1155   0.1293   1.0000
   7.000   1.3613   0.01529   0.00750  -0.1146   0.1195   1.0000
   7.250   1.3836   0.01571   0.00791  -0.1138   0.1131   1.0000
   7.500   1.4051   0.01617   0.00835  -0.1130   0.1071   1.0000
   7.750   1.4276   0.01653   0.00875  -0.1122   0.1035   1.0000
   8.000   1.4496   0.01691   0.00914  -0.1115   0.0973   1.0000
   8.250   1.4699   0.01741   0.00962  -0.1104   0.0881   1.0000
   8.750   1.5020   0.01896   0.01097  -0.1071   0.0548   1.0000
   9.000   1.5184   0.01963   0.01165  -0.1055   0.0499   1.0000
   9.250   1.5351   0.02016   0.01223  -0.1039   0.0459   1.0000
   9.500   1.5484   0.02084   0.01293  -0.1018   0.0403   1.0000
   9.750   1.5556   0.02194   0.01394  -0.0989   0.0210   1.0000
  10.000   1.5631   0.02307   0.01505  -0.0962   0.0159   1.0000
  10.250   1.5729   0.02408   0.01613  -0.0939   0.0141   1.0000
  10.500   1.5819   0.02519   0.01732  -0.0918   0.0127   1.0000
  10.750   1.5931   0.02620   0.01841  -0.0900   0.0120   1.0000
  11.000   1.6029   0.02734   0.01965  -0.0882   0.0114   1.0000
  11.250   1.6116   0.02862   0.02102  -0.0865   0.0108   1.0000
  11.500   1.6188   0.03007   0.02256  -0.0847   0.0103   1.0000
  11.750   1.6242   0.03174   0.02433  -0.0830   0.0098   1.0000
  12.000   1.6268   0.03372   0.02642  -0.0812   0.0094   1.0000
  12.250   1.6331   0.03543   0.02822  -0.0798   0.0091   1.0000
  12.500   1.6385   0.03728   0.03019  -0.0786   0.0088   1.0000
  12.750   1.6424   0.03932   0.03233  -0.0774   0.0085   1.0000
  13.000   1.6452   0.04157   0.03468  -0.0763   0.0082   1.0000
  13.250   1.6469   0.04399   0.03721  -0.0754   0.0079   1.0000
  13.500   1.6473   0.04662   0.03994  -0.0746   0.0076   1.0000
  13.750   1.6462   0.04950   0.04293  -0.0739   0.0075   1.0000
  14.000   1.6434   0.05268   0.04622  -0.0734   0.0073   1.0000
  14.250   1.6387   0.05618   0.04984  -0.0730   0.0071   1.0000
  14.500   1.6320   0.06004   0.05382  -0.0728   0.0070   1.0000
  14.750   1.6227   0.06440   0.05830  -0.0729   0.0068   1.0000
  15.000   1.6112   0.06921   0.06324  -0.0732   0.0067   1.0000
  15.250   1.6047   0.07341   0.06757  -0.0736   0.0067   1.0000
  15.500   1.5973   0.07787   0.07215  -0.0742   0.0066   1.0000
  15.750   1.5889   0.08262   0.07703  -0.0751   0.0065   1.0000
  16.000   1.5799   0.08753   0.08207  -0.0760   0.0064   1.0000
  16.250   1.5702   0.09267   0.08733  -0.0772   0.0064   1.0000
  16.500   1.5603   0.09792   0.09272  -0.0786   0.0063   1.0000
  16.750   1.5502   0.10328   0.09820  -0.0801   0.0062   1.0000
  17.000   1.5399   0.10868   0.10372  -0.0817   0.0061   1.0000
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