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GOE 365 AIRFOIL (goe365-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 365 AIRFOIL (goe365-il)
Reynolds number: 1,000,000
Max Cl/Cd: 120.66 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe365-il-1000000.txt
Download as CSV file: xf-goe365-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 365 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2219   0.09661   0.09499  -0.0589   0.9876   0.0158
  -9.750  -0.2107   0.09248   0.09086  -0.0624   0.9807   0.0158
  -9.500  -0.2031   0.08749   0.08588  -0.0660   0.9705   0.0159
  -9.250  -0.1822   0.08450   0.08287  -0.0690   0.9603   0.0161
  -9.000  -0.1534   0.08123   0.07957  -0.0747   0.9491   0.0165
  -8.250  -0.0675   0.06118   0.05911  -0.1142   0.8711   0.0191
  -7.500  -0.0817   0.04935   0.04684  -0.1163   0.8027   0.0194
  -7.250  -0.0723   0.04769   0.04510  -0.1158   0.7914   0.0196
  -7.000  -0.0619   0.04576   0.04309  -0.1155   0.7822   0.0198
  -6.500  -0.0375   0.04180   0.03894  -0.1149   0.7649   0.0207
  -6.000  -0.0275   0.02995   0.02632  -0.1121   0.7523   0.0232
  -5.750  -0.0097   0.02871   0.02504  -0.1115   0.7469   0.0235
  -5.500   0.0097   0.02769   0.02392  -0.1108   0.7422   0.0238
  -5.250   0.0301   0.02658   0.02274  -0.1102   0.7383   0.0242
  -5.000   0.0511   0.02546   0.02153  -0.1095   0.7343   0.0252
  -4.750   0.0736   0.02376   0.01934  -0.1073   0.7303   0.0275
  -4.500   0.0856   0.01975   0.01501  -0.1054   0.7264   0.0282
  -4.250   0.1090   0.01888   0.01412  -0.1050   0.7229   0.0286
  -4.000   0.1328   0.01810   0.01329  -0.1045   0.7193   0.0292
  -3.750   0.1570   0.01740   0.01250  -0.1039   0.7156   0.0303
  -3.500   0.1852   0.01802   0.01286  -0.1030   0.7117   0.0329
  -3.250   0.2043   0.01514   0.00967  -0.1017   0.7082   0.0339
  -3.000   0.2296   0.01432   0.00886  -0.1013   0.7046   0.0345
  -2.750   0.2553   0.01370   0.00821  -0.1009   0.7008   0.0353
  -2.500   0.2811   0.01321   0.00764  -0.1005   0.6967   0.0366
  -2.250   0.3092   0.01412   0.00844  -0.1000   0.6914   0.0396
  -2.000   0.3335   0.01144   0.00547  -0.0988   0.6863   0.0334
  -1.750   0.3592   0.01059   0.00461  -0.0982   0.6805   0.0319
  -1.500   0.3852   0.01014   0.00410  -0.0977   0.6753   0.0319
  -1.250   0.4112   0.00975   0.00370  -0.0972   0.6691   0.0322
  -1.000   0.4370   0.00964   0.00352  -0.0966   0.6612   0.0328
  -0.750   0.4630   0.00940   0.00327  -0.0961   0.6520   0.0330
  -0.500   0.4870   0.00897   0.00281  -0.0952   0.6438   0.0333
  -0.250   0.5115   0.00859   0.00243  -0.0944   0.6356   0.0337
   0.000   0.5362   0.00838   0.00219  -0.0937   0.6276   0.0343
   0.250   0.5614   0.00823   0.00202  -0.0931   0.6174   0.0349
   0.500   0.5868   0.00814   0.00190  -0.0925   0.6058   0.0355
   0.750   0.6117   0.00810   0.00182  -0.0918   0.5917   0.0368
   1.000   0.6354   0.00811   0.00175  -0.0909   0.5717   0.0379
   1.250   0.6593   0.00816   0.00171  -0.0900   0.5528   0.0389
   1.500   0.6822   0.00827   0.00172  -0.0889   0.5271   0.0398
   1.750   0.7052   0.00836   0.00170  -0.0879   0.5065   0.0422
   2.000   0.7289   0.00846   0.00173  -0.0870   0.4878   0.0459
   2.250   0.7517   0.00853   0.00181  -0.0860   0.4677   0.0857
   2.500   0.8567   0.00710   0.00234  -0.1041   0.4350   1.0000
   2.750   0.8768   0.00728   0.00242  -0.1025   0.4198   1.0000
   3.000   0.8969   0.00746   0.00252  -0.1009   0.4045   1.0000
   3.250   0.9172   0.00764   0.00263  -0.0994   0.3899   1.0000
   3.500   0.9373   0.00784   0.00274  -0.0979   0.3750   1.0000
   3.750   0.9573   0.00804   0.00287  -0.0963   0.3598   1.0000
   4.000   0.9770   0.00826   0.00300  -0.0947   0.3432   1.0000
   4.250   0.9963   0.00851   0.00315  -0.0930   0.3260   1.0000
   4.500   1.0150   0.00877   0.00333  -0.0913   0.3081   1.0000
   4.750   1.0337   0.00905   0.00351  -0.0895   0.2896   1.0000
   5.000   1.0522   0.00934   0.00370  -0.0877   0.2715   1.0000
   5.250   1.0705   0.00964   0.00391  -0.0859   0.2546   1.0000
   5.500   1.0890   0.00993   0.00413  -0.0842   0.2405   1.0000
   5.750   1.1076   0.01022   0.00435  -0.0825   0.2284   1.0000
   6.250   1.1458   0.01073   0.00478  -0.0793   0.2111   1.0000
   6.500   1.1641   0.01101   0.00502  -0.0776   0.2039   1.0000
   6.750   1.1838   0.01122   0.00523  -0.0761   0.1994   1.0000
   7.000   1.2010   0.01146   0.00546  -0.0741   0.1943   1.0000
   7.250   1.2166   0.01174   0.00572  -0.0718   0.1889   1.0000
   7.500   1.2351   0.01194   0.00593  -0.0702   0.1861   1.0000
   7.750   1.2525   0.01219   0.00618  -0.0683   0.1812   1.0000
   8.000   1.2687   0.01252   0.00648  -0.0664   0.1756   1.0000
   8.250   1.2875   0.01275   0.00674  -0.0649   0.1723   1.0000
   8.500   1.3061   0.01301   0.00701  -0.0634   0.1688   1.0000
   8.750   1.3235   0.01334   0.00732  -0.0618   0.1646   1.0000
   9.000   1.3406   0.01368   0.00766  -0.0601   0.1593   1.0000
   9.250   1.3595   0.01397   0.00797  -0.0588   0.1557   1.0000
   9.500   1.3764   0.01434   0.00834  -0.0572   0.1507   1.0000
   9.750   1.3933   0.01474   0.00874  -0.0557   0.1452   1.0000
  10.000   1.4099   0.01516   0.00915  -0.0542   0.1377   1.0000
  10.250   1.4252   0.01566   0.00964  -0.0526   0.1289   1.0000
  10.500   1.4339   0.01653   0.01036  -0.0502   0.1078   1.0000
  10.750   1.4401   0.01759   0.01131  -0.0475   0.0913   1.0000
  11.000   1.4504   0.01847   0.01216  -0.0455   0.0838   1.0000
  11.250   1.4603   0.01940   0.01309  -0.0436   0.0781   1.0000
  11.500   1.4739   0.02015   0.01387  -0.0423   0.0734   1.0000
  11.750   1.4815   0.02130   0.01499  -0.0403   0.0626   1.0000
  12.000   1.4668   0.02408   0.01752  -0.0364   0.0263   1.0000
  12.250   1.4718   0.02558   0.01905  -0.0346   0.0211   1.0000
  12.500   1.4775   0.02710   0.02060  -0.0330   0.0184   1.0000
  12.750   1.4871   0.02834   0.02191  -0.0319   0.0173   1.0000
  13.000   1.4942   0.02982   0.02343  -0.0307   0.0163   1.0000
  13.250   1.4986   0.03156   0.02524  -0.0293   0.0152   1.0000
  13.500   1.5057   0.03311   0.02685  -0.0283   0.0145   1.0000
  13.750   1.5125   0.03471   0.02853  -0.0274   0.0140   1.0000
  14.000   1.5181   0.03646   0.03035  -0.0264   0.0134   1.0000
  14.250   1.5214   0.03847   0.03242  -0.0255   0.0128   1.0000
  14.500   1.5209   0.04088   0.03491  -0.0246   0.0122   1.0000
  14.750   1.5186   0.04356   0.03770  -0.0237   0.0119   1.0000
  15.000   1.5206   0.04590   0.04012  -0.0232   0.0116   1.0000
  15.250   1.5228   0.04826   0.04257  -0.0227   0.0114   1.0000
  15.500   1.5239   0.05078   0.04517  -0.0224   0.0111   1.0000
  15.750   1.5227   0.05369   0.04816  -0.0222   0.0108   1.0000
  16.000   1.5215   0.05665   0.05121  -0.0221   0.0105   1.0000
  16.250   1.5162   0.06021   0.05487  -0.0222   0.0104   1.0000
  16.500   1.5118   0.06374   0.05848  -0.0225   0.0100   1.0000
  16.750   1.5059   0.06757   0.06241  -0.0230   0.0099   1.0000
  17.000   1.4928   0.07250   0.06746  -0.0238   0.0097   1.0000
  17.250   1.4817   0.07724   0.07230  -0.0247   0.0096   1.0000
  17.500   1.4651   0.08288   0.07807  -0.0260   0.0095   1.0000
  17.750   1.4420   0.08964   0.08498  -0.0277   0.0093   1.0000
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