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GOE 415 AIRFOIL (goe415-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 415 AIRFOIL (goe415-il)
Reynolds number: 1,000,000
Max Cl/Cd: 109.75 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe415-il-1000000.txt
Download as CSV file: xf-goe415-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 415 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4241   0.09030   0.08883  -0.0047   1.0000   0.0077
  -7.750  -0.4191   0.08657   0.08512  -0.0071   1.0000   0.0077
  -7.500  -0.4142   0.08277   0.08134  -0.0100   1.0000   0.0078
  -7.250  -0.4043   0.07837   0.07695  -0.0146   1.0000   0.0078
  -7.000  -0.3918   0.07363   0.07222  -0.0200   1.0000   0.0078
  -6.750  -0.3775   0.06865   0.06723  -0.0256   1.0000   0.0078
  -6.500  -0.3622   0.06353   0.06209  -0.0308   1.0000   0.0078
  -6.250  -0.3466   0.05833   0.05685  -0.0354   0.9996   0.0078
  -6.000  -0.3189   0.04829   0.04665  -0.0464   0.9896   0.0082
  -5.750  -0.2895   0.04414   0.04239  -0.0513   0.9789   0.0084
  -5.500  -0.2597   0.04017   0.03827  -0.0554   0.9646   0.0088
  -5.250  -0.2319   0.03616   0.03406  -0.0581   0.9470   0.0097
  -5.000  -0.2000   0.03276   0.03032  -0.0583   0.9305   0.0114
  -4.750  -0.1763   0.02949   0.02672  -0.0584   0.9153   0.0115
  -3.500  -0.0557   0.01488   0.01028  -0.0563   0.8198   0.0119
  -3.250  -0.0314   0.01252   0.00746  -0.0551   0.7649   0.0107
  -3.000  -0.0056   0.01181   0.00636  -0.0543   0.7125   0.0114
  -2.750   0.0198   0.01026   0.00449  -0.0536   0.6754   0.0123
  -2.500   0.0463   0.00985   0.00391  -0.0532   0.6390   0.0130
  -2.250   0.0733   0.00968   0.00360  -0.0529   0.6055   0.0139
  -2.000   0.1005   0.00953   0.00330  -0.0527   0.5772   0.0153
  -1.750   0.1279   0.00931   0.00296  -0.0524   0.5555   0.0165
  -1.500   0.1547   0.00872   0.00222  -0.0521   0.5383   0.0183
  -1.250   0.1824   0.00854   0.00199  -0.0520   0.5244   0.0204
  -1.000   0.2103   0.00848   0.00187  -0.0519   0.5124   0.0234
  -0.750   0.2382   0.00842   0.00174  -0.0518   0.5013   0.0252
  -0.250   0.2939   0.00809   0.00125  -0.0515   0.4799   0.0351
   0.000   0.3219   0.00803   0.00112  -0.0514   0.4694   0.0427
   0.250   0.3481   0.00729   0.00108  -0.0515   0.4585   0.3136
   0.500   0.3742   0.00682   0.00112  -0.0514   0.4465   0.5127
   0.750   0.4101   0.00566   0.00117  -0.0532   0.4316   1.0000
   1.000   0.4374   0.00576   0.00117  -0.0530   0.4171   1.0000
   1.250   0.4648   0.00587   0.00119  -0.0528   0.4031   1.0000
   1.500   0.4922   0.00599   0.00121  -0.0526   0.3884   1.0000
   1.750   0.5195   0.00611   0.00125  -0.0525   0.3742   1.0000
   2.000   0.5469   0.00624   0.00130  -0.0523   0.3615   1.0000
   2.250   0.5742   0.00638   0.00136  -0.0522   0.3493   1.0000
   2.500   0.6015   0.00651   0.00143  -0.0521   0.3378   1.0000
   2.750   0.6289   0.00664   0.00151  -0.0520   0.3269   1.0000
   3.000   0.6562   0.00679   0.00159  -0.0518   0.3157   1.0000
   3.250   0.6834   0.00694   0.00169  -0.0517   0.3050   1.0000
   3.500   0.7107   0.00709   0.00178  -0.0516   0.2960   1.0000
   3.750   0.7381   0.00722   0.00190  -0.0515   0.2886   1.0000
   4.250   0.7926   0.00752   0.00213  -0.0513   0.2714   1.0000
   4.500   0.8197   0.00769   0.00226  -0.0512   0.2609   1.0000
   4.750   0.8467   0.00787   0.00242  -0.0511   0.2523   1.0000
   5.000   0.8737   0.00804   0.00256  -0.0510   0.2412   1.0000
   5.250   0.9006   0.00824   0.00271  -0.0509   0.2289   1.0000
   5.500   0.9274   0.00845   0.00288  -0.0508   0.2164   1.0000
   5.750   0.9535   0.00876   0.00310  -0.0506   0.1955   1.0000
   6.000   0.9770   0.00947   0.00349  -0.0502   0.1378   1.0000
   6.250   0.9988   0.01050   0.00416  -0.0496   0.0802   1.0000
   6.500   1.0192   0.01182   0.00515  -0.0486   0.0143   1.0000
   6.750   1.0450   0.01217   0.00559  -0.0483   0.0126   1.0000
   7.000   1.0703   0.01259   0.00608  -0.0480   0.0113   1.0000
   7.250   1.0950   0.01311   0.00666  -0.0476   0.0101   1.0000
   7.500   1.1182   0.01387   0.00754  -0.0469   0.0090   1.0000
   7.750   1.1400   0.01484   0.00866  -0.0461   0.0083   1.0000
   8.000   1.1645   0.01527   0.00915  -0.0457   0.0078   1.0000
   8.250   1.1881   0.01584   0.00978  -0.0452   0.0072   1.0000
   8.500   1.2103   0.01658   0.01060  -0.0445   0.0067   1.0000
   8.750   1.2317   0.01739   0.01148  -0.0437   0.0063   1.0000
   9.000   1.2521   0.01827   0.01244  -0.0429   0.0060   1.0000
   9.250   1.2704   0.01934   0.01359  -0.0418   0.0057   1.0000
   9.500   1.2821   0.02109   0.01547  -0.0400   0.0054   1.0000
   9.750   1.2843   0.02380   0.01831  -0.0371   0.0051   1.0000
  10.000   1.3037   0.02447   0.01907  -0.0362   0.0050   1.0000
  10.250   1.3179   0.02566   0.02035  -0.0347   0.0048   1.0000
  10.500   1.3281   0.02718   0.02198  -0.0328   0.0047   1.0000
  10.750   1.3354   0.02870   0.02359  -0.0305   0.0045   1.0000
  11.000   1.3408   0.03019   0.02518  -0.0282   0.0044   1.0000
  11.250   1.3450   0.03186   0.02696  -0.0262   0.0042   1.0000
  11.500   1.3483   0.03372   0.02892  -0.0245   0.0041   1.0000
  11.750   1.3497   0.03599   0.03131  -0.0231   0.0040   1.0000
  12.000   1.3496   0.03861   0.03406  -0.0219   0.0040   1.0000
  12.250   1.3492   0.04140   0.03700  -0.0211   0.0039   1.0000
  12.500   1.3468   0.04463   0.04038  -0.0206   0.0039   1.0000
  12.750   1.3440   0.04803   0.04392  -0.0206   0.0039   1.0000
  13.000   1.3386   0.05195   0.04800  -0.0208   0.0039   1.0000
  13.250   1.3320   0.05612   0.05233  -0.0217   0.0039   1.0000
  13.500   1.3232   0.06076   0.05713  -0.0230   0.0039   1.0000
  13.750   1.3131   0.06574   0.06227  -0.0248   0.0039   1.0000
  14.000   1.3007   0.07120   0.06789  -0.0269   0.0040   1.0000
  14.250   1.2878   0.07685   0.07369  -0.0294   0.0040   1.0000
  14.500   1.2711   0.08327   0.08027  -0.0323   0.0040   1.0000
  14.750   1.2566   0.08957   0.08671  -0.0354   0.0040   1.0000
  15.000   1.2392   0.09662   0.09391  -0.0390   0.0041   1.0000
  15.250   1.2230   0.10382   0.10125  -0.0428   0.0041   1.0000
  15.500   1.2073   0.11122   0.10877  -0.0469   0.0041   1.0000
  15.750   1.1904   0.11910   0.11678  -0.0513   0.0042   1.0000
  16.000   1.1737   0.12732   0.12513  -0.0560   0.0043   1.0000
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