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GOE 407 AIRFOIL (goe407-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 407 AIRFOIL (goe407-il)
Reynolds number: 500,000
Max Cl/Cd: 95.58 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe407-il-500000-n5.txt
Download as CSV file: xf-goe407-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 407 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2624   0.09212   0.08973  -0.0484   0.9879   0.0187
  -8.750  -0.2605   0.08544   0.08305  -0.0565   0.9847   0.0192
  -8.500  -0.2528   0.08190   0.07952  -0.0591   0.9800   0.0192
  -8.250  -0.2264   0.08237   0.08000  -0.0578   0.9779   0.0204
  -7.750  -0.2100   0.07526   0.07289  -0.0647   0.9662   0.0207
  -7.250  -0.1894   0.06689   0.06449  -0.0743   0.9485   0.0226
  -7.000  -0.1780   0.06328   0.06085  -0.0771   0.9367   0.0225
  -6.750  -0.1606   0.05976   0.05728  -0.0804   0.9227   0.0220
  -6.500  -0.1280   0.05001   0.04725  -0.0932   0.9008   0.0231
  -6.250  -0.0837   0.04705   0.04417  -0.1005   0.8796   0.0236
  -6.000  -0.0397   0.04604   0.04300  -0.1058   0.8503   0.0253
  -5.750  -0.0209   0.04257   0.03924  -0.1076   0.8210   0.0253
  -5.500  -0.0084   0.03929   0.03571  -0.1073   0.8021   0.0248
  -5.250   0.0038   0.03602   0.03220  -0.1063   0.7877   0.0245
  -5.000   0.0155   0.03248   0.02839  -0.1047   0.7751   0.0242
  -4.750   0.0311   0.03039   0.02611  -0.1032   0.7631   0.0245
  -4.500   0.0468   0.02818   0.02369  -0.1014   0.7513   0.0249
  -4.250   0.0605   0.02534   0.02056  -0.0991   0.7388   0.0250
  -4.000   0.0735   0.02231   0.01716  -0.0962   0.7258   0.0250
  -3.750   0.0876   0.01973   0.01419  -0.0934   0.7118   0.0252
  -3.250   0.1227   0.01625   0.00997  -0.0889   0.6836   0.0255
  -3.000   0.1440   0.01532   0.00879  -0.0874   0.6719   0.0260
  -2.750   0.1665   0.01456   0.00778  -0.0861   0.6629   0.0264
  -2.500   0.1901   0.01382   0.00685  -0.0851   0.6551   0.0266
  -2.250   0.2141   0.01326   0.00611  -0.0842   0.6481   0.0267
  -2.000   0.2391   0.01278   0.00550  -0.0834   0.6412   0.0270
  -1.750   0.2639   0.01241   0.00501  -0.0826   0.6345   0.0273
  -1.500   0.2890   0.01209   0.00460  -0.0819   0.6282   0.0274
  -1.250   0.3143   0.01184   0.00428  -0.0812   0.6218   0.0276
  -0.750   0.3634   0.01108   0.00343  -0.0797   0.6090   0.0283
  -0.500   0.3877   0.01085   0.00318  -0.0788   0.6021   0.0287
  -0.250   0.4121   0.01067   0.00299  -0.0780   0.5958   0.0293
   0.000   0.4367   0.01052   0.00284  -0.0772   0.5885   0.0299
   0.250   0.4607   0.01041   0.00270  -0.0763   0.5816   0.0307
   0.500   0.4854   0.01026   0.00256  -0.0755   0.5741   0.0311
   0.750   0.5093   0.01018   0.00244  -0.0746   0.5666   0.0314
   1.000   0.5339   0.01008   0.00235  -0.0738   0.5585   0.0320
   1.250   0.5576   0.01004   0.00227  -0.0728   0.5491   0.0326
   1.500   0.5817   0.01001   0.00222  -0.0719   0.5369   0.0332
   1.750   0.6049   0.00998   0.00216  -0.0708   0.5227   0.0341
   2.000   0.6272   0.01000   0.00212  -0.0695   0.5044   0.0356
   2.250   0.6488   0.01008   0.00212  -0.0682   0.4825   0.0372
   2.750   0.6892   0.01035   0.00226  -0.0649   0.4326   0.0692
   3.000   0.7097   0.01051   0.00237  -0.0634   0.4119   0.0918
   3.250   0.7303   0.01051   0.00252  -0.0620   0.3972   0.1854
   3.750   0.9489   0.01012   0.00362  -0.0999   0.3474   1.0000
   4.500   1.0148   0.01070   0.00407  -0.0964   0.3192   1.0000
   4.750   1.0362   0.01091   0.00424  -0.0951   0.3114   1.0000
   5.000   1.0583   0.01109   0.00441  -0.0939   0.3037   1.0000
   5.250   1.0791   0.01132   0.00461  -0.0925   0.2950   1.0000
   5.500   1.1002   0.01153   0.00480  -0.0912   0.2850   1.0000
   5.750   1.1210   0.01175   0.00500  -0.0898   0.2787   1.0000
   6.000   1.1422   0.01195   0.00520  -0.0885   0.2716   1.0000
   6.250   1.1621   0.01221   0.00544  -0.0870   0.2644   1.0000
   6.500   1.1826   0.01243   0.00566  -0.0856   0.2556   1.0000
   6.750   1.2018   0.01270   0.00592  -0.0840   0.2482   1.0000
   7.000   1.2214   0.01295   0.00617  -0.0824   0.2385   1.0000
   7.250   1.2386   0.01330   0.00646  -0.0804   0.2232   1.0000
   7.500   1.2545   0.01370   0.00679  -0.0782   0.2054   1.0000
   7.750   1.2689   0.01417   0.00715  -0.0758   0.1832   1.0000
   8.000   1.2746   0.01504   0.00774  -0.0718   0.1372   1.0000
   8.250   1.2819   0.01566   0.00826  -0.0681   0.1205   1.0000
   8.500   1.2928   0.01609   0.00868  -0.0649   0.1128   1.0000
   8.750   1.3033   0.01656   0.00914  -0.0618   0.1064   1.0000
   9.000   1.3164   0.01694   0.00955  -0.0592   0.1019   1.0000
   9.250   1.3293   0.01735   0.01000  -0.0566   0.0974   1.0000
   9.500   1.3405   0.01787   0.01052  -0.0538   0.0922   1.0000
   9.750   1.3537   0.01830   0.01099  -0.0514   0.0877   1.0000
  10.000   1.3664   0.01878   0.01149  -0.0490   0.0826   1.0000
  10.250   1.3774   0.01937   0.01208  -0.0464   0.0769   1.0000
  10.500   1.3894   0.01993   0.01265  -0.0440   0.0707   1.0000
  10.750   1.3992   0.02062   0.01334  -0.0414   0.0633   1.0000
  11.000   1.4060   0.02151   0.01417  -0.0385   0.0517   1.0000
  11.250   1.4095   0.02264   0.01522  -0.0354   0.0389   1.0000
  11.500   1.4066   0.02422   0.01670  -0.0317   0.0228   1.0000
  11.750   1.4095   0.02553   0.01803  -0.0289   0.0186   1.0000
  12.000   1.4146   0.02677   0.01934  -0.0266   0.0167   1.0000
  12.250   1.4210   0.02800   0.02063  -0.0246   0.0157   1.0000
  12.500   1.4255   0.02944   0.02215  -0.0226   0.0147   1.0000
  12.750   1.4295   0.03100   0.02379  -0.0208   0.0139   1.0000
  13.000   1.4333   0.03265   0.02552  -0.0192   0.0132   1.0000
  13.250   1.4381   0.03429   0.02725  -0.0178   0.0128   1.0000
  13.500   1.4424   0.03603   0.02909  -0.0166   0.0124   1.0000
  13.750   1.4449   0.03799   0.03115  -0.0154   0.0119   1.0000
  14.000   1.4460   0.04018   0.03342  -0.0144   0.0115   1.0000
  14.250   1.4457   0.04258   0.03591  -0.0135   0.0110   1.0000
  14.500   1.4435   0.04527   0.03870  -0.0127   0.0108   1.0000
  14.750   1.4387   0.04836   0.04188  -0.0121   0.0104   1.0000
  15.000   1.4368   0.05120   0.04483  -0.0117   0.0103   1.0000
  15.250   1.4357   0.05401   0.04775  -0.0114   0.0101   1.0000
  15.500   1.4321   0.05720   0.05106  -0.0113   0.0098   1.0000
  15.750   1.4274   0.06063   0.05460  -0.0114   0.0097   1.0000
  16.000   1.4225   0.06420   0.05828  -0.0116   0.0095   1.0000
  16.250   1.4144   0.06830   0.06249  -0.0121   0.0094   1.0000
  16.500   1.4077   0.07234   0.06665  -0.0128   0.0093   1.0000
  16.750   1.4004   0.07659   0.07101  -0.0136   0.0091   1.0000
  17.000   1.3921   0.08107   0.07559  -0.0146   0.0089   1.0000
  17.250   1.3841   0.08560   0.08024  -0.0158   0.0088   1.0000
  17.500   1.3737   0.09061   0.08536  -0.0171   0.0087   1.0000
  17.750   1.3643   0.09551   0.09037  -0.0186   0.0086   1.0000
  18.000   1.3537   0.10063   0.09559  -0.0202   0.0085   1.0000
  18.250   1.3439   0.10567   0.10074  -0.0218   0.0084   1.0000
  18.500   1.3335   0.11090   0.10607  -0.0236   0.0083   1.0000
  18.750   1.3225   0.11629   0.11156  -0.0256   0.0083   1.0000
  19.000   1.3112   0.12176   0.11712  -0.0277   0.0081   1.0000
  19.250   1.3003   0.12724   0.12267  -0.0299   0.0079   1.0000
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