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GOE 613 AIRFOIL (goe613-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 613 AIRFOIL (goe613-il)
Reynolds number: 1,000,000
Max Cl/Cd: 112.02 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe613-il-1000000.txt
Download as CSV file: xf-goe613-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 613 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3497   0.11035   0.10874  -0.0329   1.0000   0.0156
 -10.250  -0.3519   0.10726   0.10566  -0.0328   1.0000   0.0156
 -10.000  -0.3571   0.10413   0.10257  -0.0322   1.0000   0.0156
  -9.750  -0.3535   0.09806   0.09650  -0.0362   0.9991   0.0158
  -9.500  -0.3345   0.09620   0.09463  -0.0378   0.9982   0.0161
  -9.250  -0.3176   0.09343   0.09186  -0.0409   0.9968   0.0165
  -9.000  -0.3029   0.08986   0.08829  -0.0448   0.9952   0.0170
  -8.750  -0.2936   0.08358   0.08202  -0.0530   0.9919   0.0194
  -7.500  -0.2307   0.05351   0.05181  -0.0913   0.9661   0.0204
  -7.250  -0.2055   0.05231   0.05058  -0.0934   0.9623   0.0210
  -7.000  -0.1755   0.04802   0.04619  -0.0999   0.9591   0.0225
  -6.750  -0.1513   0.03831   0.03607  -0.1068   0.9486   0.0243
  -6.500  -0.1396   0.03280   0.03033  -0.1089   0.9395   0.0234
  -6.250  -0.1231   0.02811   0.02529  -0.1095   0.9306   0.0255
  -6.000  -0.0987   0.02821   0.02539  -0.1096   0.9232   0.0262
  -5.750  -0.0747   0.02695   0.02399  -0.1098   0.9155   0.0274
  -5.500  -0.0496   0.02608   0.02280  -0.1082   0.9067   0.0304
  -5.250  -0.0316   0.02381   0.02023  -0.1070   0.8978   0.0304
  -5.000  -0.0187   0.02011   0.01623  -0.1052   0.8870   0.0301
  -4.750   0.0021   0.01890   0.01477  -0.1038   0.8763   0.0304
  -4.500   0.0235   0.01765   0.01326  -0.1026   0.8661   0.0305
  -4.250   0.0426   0.01534   0.01063  -0.1011   0.8557   0.0306
  -4.000   0.0657   0.01427   0.00940  -0.1001   0.8454   0.0306
  -3.750   0.0898   0.01336   0.00833  -0.0993   0.8356   0.0305
  -3.500   0.1131   0.01196   0.00673  -0.0984   0.8254   0.0307
  -3.250   0.1366   0.01064   0.00526  -0.0975   0.8137   0.0311
  -3.000   0.1609   0.00994   0.00450  -0.0968   0.8015   0.0321
  -2.750   0.1857   0.00959   0.00408  -0.0961   0.7885   0.0326
  -2.500   0.2106   0.00931   0.00373  -0.0953   0.7759   0.0332
  -2.250   0.2354   0.00906   0.00342  -0.0946   0.7634   0.0337
  -2.000   0.2601   0.00882   0.00310  -0.0938   0.7512   0.0342
  -1.750   0.2849   0.00857   0.00281  -0.0931   0.7395   0.0347
  -1.500   0.3098   0.00838   0.00256  -0.0924   0.7279   0.0353
  -1.250   0.3345   0.00822   0.00235  -0.0916   0.7158   0.0359
  -1.000   0.3594   0.00811   0.00218  -0.0909   0.7031   0.0369
  -0.750   0.3846   0.00807   0.00209  -0.0902   0.6899   0.0378
  -0.500   0.4096   0.00801   0.00198  -0.0895   0.6750   0.0382
  -0.250   0.4331   0.00776   0.00164  -0.0885   0.6574   0.0401
   0.000   0.4568   0.00772   0.00152  -0.0876   0.6333   0.0418
   0.250   0.4795   0.00779   0.00145  -0.0864   0.5991   0.0437
   0.500   0.5014   0.00792   0.00143  -0.0851   0.5625   0.0459
   0.750   0.5247   0.00805   0.00143  -0.0841   0.5371   0.0481
   1.000   0.5486   0.00809   0.00140  -0.0833   0.5184   0.0565
   1.250   0.5681   0.00754   0.00146  -0.0819   0.5034   0.3227
   1.500   0.6242   0.00623   0.00180  -0.0885   0.4844   0.9823
   1.750   0.6854   0.00647   0.00191  -0.0960   0.4643   0.9972
   2.000   0.7246   0.00663   0.00196  -0.0986   0.4444   1.0000
   2.250   0.7457   0.00678   0.00201  -0.0972   0.4272   1.0000
   2.500   0.7665   0.00694   0.00208  -0.0958   0.4089   1.0000
   3.000   0.8084   0.00730   0.00226  -0.0930   0.3750   1.0000
   3.250   0.8296   0.00748   0.00236  -0.0916   0.3601   1.0000
   3.500   0.8507   0.00767   0.00247  -0.0902   0.3467   1.0000
   4.000   0.8935   0.00805   0.00272  -0.0876   0.3197   1.0000
   4.250   0.9152   0.00824   0.00285  -0.0864   0.3077   1.0000
   4.500   0.9370   0.00842   0.00299  -0.0852   0.2975   1.0000
   4.750   0.9585   0.00863   0.00313  -0.0840   0.2858   1.0000
   5.000   0.9808   0.00880   0.00327  -0.0829   0.2766   1.0000
   5.250   1.0031   0.00897   0.00341  -0.0818   0.2687   1.0000
   5.500   1.0251   0.00917   0.00358  -0.0807   0.2599   1.0000
   5.750   1.0474   0.00935   0.00373  -0.0796   0.2505   1.0000
   6.000   1.0689   0.00957   0.00390  -0.0784   0.2399   1.0000
   6.250   1.0900   0.00982   0.00409  -0.0772   0.2277   1.0000
   6.500   1.1107   0.01008   0.00430  -0.0759   0.2142   1.0000
   6.750   1.1307   0.01040   0.00453  -0.0745   0.1956   1.0000
   7.000   1.1449   0.01105   0.00491  -0.0721   0.1530   1.0000
   7.250   1.1478   0.01240   0.00578  -0.0678   0.0799   1.0000
   7.500   1.1505   0.01380   0.00683  -0.0634   0.0179   1.0000
   7.750   1.1688   0.01415   0.00721  -0.0617   0.0160   1.0000
   8.000   1.1857   0.01451   0.00761  -0.0597   0.0150   1.0000
   8.250   1.2015   0.01492   0.00807  -0.0576   0.0140   1.0000
   8.500   1.2150   0.01549   0.00869  -0.0551   0.0128   1.0000
   8.750   1.2297   0.01601   0.00928  -0.0528   0.0122   1.0000
   9.000   1.2457   0.01645   0.00976  -0.0509   0.0119   1.0000
   9.250   1.2613   0.01693   0.01029  -0.0489   0.0114   1.0000
   9.500   1.2759   0.01748   0.01088  -0.0469   0.0110   1.0000
   9.750   1.2891   0.01811   0.01157  -0.0447   0.0105   1.0000
  10.000   1.3014   0.01881   0.01232  -0.0425   0.0101   1.0000
  10.250   1.3113   0.01965   0.01322  -0.0400   0.0097   1.0000
  10.500   1.3172   0.02074   0.01440  -0.0370   0.0095   1.0000
  10.750   1.3143   0.02239   0.01618  -0.0332   0.0092   1.0000
  11.000   1.3293   0.02301   0.01684  -0.0318   0.0090   1.0000
  11.250   1.3374   0.02407   0.01797  -0.0297   0.0088   1.0000
  11.500   1.3483   0.02500   0.01896  -0.0280   0.0085   1.0000
  11.750   1.3545   0.02628   0.02032  -0.0260   0.0084   1.0000
  12.000   1.3607   0.02762   0.02173  -0.0242   0.0081   1.0000
  12.250   1.3646   0.02922   0.02341  -0.0224   0.0079   1.0000
  12.500   1.3684   0.03090   0.02516  -0.0208   0.0077   1.0000
  12.750   1.3722   0.03268   0.02701  -0.0194   0.0075   1.0000
  13.000   1.3721   0.03489   0.02931  -0.0181   0.0074   1.0000
  13.250   1.3726   0.03717   0.03167  -0.0171   0.0073   1.0000
  13.500   1.3703   0.03985   0.03443  -0.0163   0.0071   1.0000
  13.750   1.3684   0.04260   0.03726  -0.0157   0.0071   1.0000
  14.000   1.3641   0.04575   0.04050  -0.0153   0.0070   1.0000
  14.250   1.3526   0.04981   0.04465  -0.0150   0.0069   1.0000
  14.500   1.3423   0.05384   0.04877  -0.0149   0.0068   1.0000
  14.750   1.3324   0.05780   0.05280  -0.0147   0.0067   1.0000
  15.000   1.3276   0.06121   0.05628  -0.0145   0.0067   1.0000
  15.250   1.3274   0.06451   0.05968  -0.0152   0.0066   1.0000
  15.500   1.3261   0.06794   0.06320  -0.0159   0.0066   1.0000
  15.750   1.3251   0.07159   0.06696  -0.0170   0.0064   1.0000
  16.000   1.3220   0.07509   0.07054  -0.0174   0.0064   1.0000
  16.250   1.3192   0.07869   0.07422  -0.0180   0.0064   1.0000
  16.500   1.3168   0.08217   0.07778  -0.0185   0.0064   1.0000
  16.750   1.3130   0.08647   0.08220  -0.0202   0.0062   1.0000
  17.000   1.3096   0.09046   0.08628  -0.0215   0.0061   1.0000
  17.250   1.3061   0.09415   0.09005  -0.0221   0.0060   1.0000
  17.500   1.3020   0.09838   0.09438  -0.0236   0.0059   1.0000
  17.750   1.2982   0.10262   0.09870  -0.0252   0.0058   1.0000
  18.000   1.2939   0.10690   0.10307  -0.0268   0.0056   1.0000
  18.250   1.2898   0.11105   0.10730  -0.0282   0.0056   1.0000
  18.500   1.2857   0.11502   0.11138  -0.0292   0.0056   1.0000
  18.750   1.2815   0.11960   0.11604  -0.0314   0.0055   1.0000
  19.000   1.2773   0.12406   0.12058  -0.0334   0.0054   1.0000
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