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GOE 425 AIRFOIL (goe425-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 425 AIRFOIL (goe425-il)
Reynolds number: 500,000
Max Cl/Cd: 108.37 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe425-il-500000-n5.txt
Download as CSV file: xf-goe425-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 425 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.5856   0.04423   0.04017  -0.0881   0.7133   0.0238
 -11.000  -0.6045   0.03991   0.03553  -0.0894   0.7074   0.0239
 -10.750  -0.6082   0.03644   0.03174  -0.0896   0.7013   0.0242
 -10.500  -0.6038   0.03364   0.02860  -0.0894   0.6953   0.0246
 -10.250  -0.5946   0.03116   0.02578  -0.0889   0.6897   0.0250
 -10.000  -0.5812   0.02910   0.02341  -0.0884   0.6834   0.0252
  -9.750  -0.5645   0.02747   0.02147  -0.0879   0.6773   0.0255
  -9.500  -0.5452   0.02615   0.01990  -0.0874   0.6717   0.0256
  -9.250  -0.5252   0.02471   0.01828  -0.0870   0.6658   0.0258
  -9.000  -0.5035   0.02357   0.01701  -0.0866   0.6600   0.0260
  -8.750  -0.4804   0.02266   0.01599  -0.0864   0.6546   0.0262
  -8.500  -0.4565   0.02187   0.01510  -0.0861   0.6485   0.0264
  -8.250  -0.4324   0.02115   0.01428  -0.0858   0.6425   0.0266
  -8.000  -0.4076   0.02050   0.01354  -0.0856   0.6366   0.0269
  -7.750  -0.3825   0.01992   0.01286  -0.0853   0.6298   0.0272
  -7.500  -0.3574   0.01934   0.01217  -0.0851   0.6234   0.0275
  -7.250  -0.3319   0.01870   0.01144  -0.0848   0.6169   0.0278
  -7.000  -0.3064   0.01809   0.01072  -0.0846   0.6105   0.0280
  -6.750  -0.2807   0.01751   0.01003  -0.0843   0.6049   0.0283
  -6.500  -0.2547   0.01696   0.00940  -0.0841   0.5987   0.0286
  -6.250  -0.2286   0.01646   0.00881  -0.0839   0.5927   0.0288
  -6.000  -0.2024   0.01600   0.00826  -0.0836   0.5874   0.0291
  -5.750  -0.1760   0.01556   0.00776  -0.0834   0.5815   0.0293
  -5.500  -0.1496   0.01518   0.00729  -0.0832   0.5757   0.0296
  -5.250  -0.1230   0.01483   0.00687  -0.0830   0.5705   0.0298
  -5.000  -0.0962   0.01450   0.00650  -0.0828   0.5654   0.0300
  -4.750  -0.0705   0.01400   0.00596  -0.0825   0.5607   0.0304
  -4.250  -0.0173   0.01338   0.00531  -0.0822   0.5525   0.0314
  -4.000   0.0098   0.01313   0.00504  -0.0820   0.5483   0.0318
  -3.750   0.0367   0.01289   0.00476  -0.0819   0.5440   0.0323
  -3.500   0.0636   0.01268   0.00450  -0.0817   0.5400   0.0327
  -3.250   0.0909   0.01247   0.00426  -0.0816   0.5367   0.0332
  -3.000   0.1185   0.01227   0.00405  -0.0815   0.5335   0.0337
  -2.750   0.1460   0.01210   0.00385  -0.0815   0.5301   0.0342
  -2.500   0.1735   0.01196   0.00367  -0.0814   0.5266   0.0346
  -2.250   0.2008   0.01181   0.00348  -0.0813   0.5233   0.0352
  -2.000   0.2284   0.01166   0.00332  -0.0812   0.5204   0.0360
  -1.750   0.2564   0.01153   0.00319  -0.0813   0.5177   0.0370
  -1.500   0.2844   0.01144   0.00309  -0.0813   0.5147   0.0383
  -1.250   0.3124   0.01137   0.00300  -0.0813   0.5115   0.0397
  -1.000   0.3403   0.01130   0.00291  -0.0813   0.5085   0.0413
  -0.750   0.3680   0.01125   0.00283  -0.0812   0.5057   0.0436
  -0.500   0.3961   0.01119   0.00276  -0.0812   0.5031   0.0471
  -0.250   0.4236   0.01097   0.00270  -0.0813   0.5003   0.0863
   0.000   0.4517   0.01092   0.00269  -0.0813   0.4974   0.1087
   0.250   0.4796   0.01086   0.00267  -0.0814   0.4943   0.1247
   0.500   0.5052   0.01040   0.00262  -0.0813   0.4914   0.2634
   0.750   0.5308   0.01005   0.00264  -0.0811   0.4887   0.3956
   1.000   0.5579   0.00993   0.00272  -0.0811   0.4863   0.4664
   1.250   0.5858   0.00988   0.00279  -0.0811   0.4838   0.5041
   1.500   0.6133   0.00984   0.00286  -0.0811   0.4809   0.5421
   1.750   0.6405   0.00979   0.00294  -0.0810   0.4780   0.5816
   2.000   0.6678   0.00977   0.00301  -0.0809   0.4754   0.6126
   2.500   0.7222   0.00982   0.00315  -0.0807   0.4704   0.6611
   3.000   0.7765   0.00974   0.00332  -0.0805   0.4649   0.7248
   3.250   0.8010   0.00959   0.00343  -0.0797   0.4621   0.7978
   3.500   0.8511   0.00945   0.00360  -0.0843   0.4590   0.9680
   3.750   0.8892   0.00958   0.00369  -0.0867   0.4555   0.9968
   4.000   0.9184   0.00969   0.00379  -0.0871   0.4521   1.0000
   4.250   0.9445   0.00978   0.00389  -0.0868   0.4483   1.0000
   4.500   0.9705   0.00989   0.00400  -0.0865   0.4447   1.0000
   4.750   0.9961   0.01002   0.00411  -0.0861   0.4412   1.0000
   5.000   1.0215   0.01017   0.00422  -0.0858   0.4374   1.0000
   5.250   1.0478   0.01027   0.00436  -0.0856   0.4332   1.0000
   5.500   1.0736   0.01039   0.00449  -0.0853   0.4290   1.0000
   5.750   1.0991   0.01054   0.00463  -0.0850   0.4250   1.0000
   6.000   1.1244   0.01070   0.00478  -0.0846   0.4206   1.0000
   6.250   1.1502   0.01082   0.00493  -0.0844   0.4150   1.0000
   6.500   1.1750   0.01099   0.00509  -0.0840   0.4088   1.0000
   6.750   1.2001   0.01117   0.00527  -0.0836   0.4035   1.0000
   7.000   1.2253   0.01133   0.00546  -0.0833   0.3979   1.0000
   7.250   1.2490   0.01156   0.00566  -0.0827   0.3910   1.0000
   7.500   1.2734   0.01175   0.00587  -0.0823   0.3827   1.0000
   7.750   1.2964   0.01201   0.00611  -0.0817   0.3756   1.0000
   8.000   1.3207   0.01222   0.00635  -0.0813   0.3694   1.0000
   8.250   1.3427   0.01252   0.00664  -0.0805   0.3609   1.0000
   8.500   1.3652   0.01280   0.00693  -0.0798   0.3521   1.0000
   8.750   1.3857   0.01317   0.00727  -0.0789   0.3433   1.0000
   9.000   1.4062   0.01353   0.00763  -0.0779   0.3325   1.0000
   9.250   1.4252   0.01394   0.00803  -0.0767   0.3218   1.0000
   9.500   1.4420   0.01443   0.00849  -0.0752   0.3108   1.0000
   9.750   1.4546   0.01502   0.00904  -0.0731   0.2965   1.0000
  10.000   1.4647   0.01575   0.00971  -0.0707   0.2783   1.0000
  10.250   1.4697   0.01679   0.01065  -0.0678   0.2540   1.0000
  10.500   1.4673   0.01836   0.01207  -0.0645   0.2221   1.0000
  10.750   1.4579   0.02062   0.01415  -0.0611   0.1875   1.0000
  11.000   1.4540   0.02284   0.01629  -0.0589   0.1687   1.0000
  11.250   1.4559   0.02483   0.01827  -0.0576   0.1581   1.0000
  11.500   1.4578   0.02696   0.02040  -0.0564   0.1495   1.0000
  11.750   1.4619   0.02896   0.02244  -0.0555   0.1418   1.0000
  12.000   1.4635   0.03123   0.02472  -0.0546   0.1350   1.0000
  12.250   1.4672   0.03333   0.02686  -0.0539   0.1277   1.0000
  12.500   1.4669   0.03580   0.02934  -0.0530   0.1207   1.0000
  12.750   1.4676   0.03821   0.03178  -0.0522   0.1132   1.0000
  13.000   1.4656   0.04089   0.03448  -0.0514   0.1058   1.0000
  13.250   1.4612   0.04385   0.03744  -0.0506   0.0979   1.0000
  13.500   1.4587   0.04671   0.04031  -0.0499   0.0917   1.0000
  13.750   1.4547   0.04979   0.04341  -0.0494   0.0865   1.0000
  14.000   1.4547   0.05252   0.04618  -0.0490   0.0828   1.0000
  14.250   1.4535   0.05544   0.04914  -0.0486   0.0793   1.0000
  14.500   1.4500   0.05864   0.05237  -0.0483   0.0758   1.0000
  14.750   1.4514   0.06132   0.05511  -0.0481   0.0728   1.0000
  15.000   1.4513   0.06422   0.05806  -0.0480   0.0696   1.0000
  15.250   1.4488   0.06743   0.06130  -0.0479   0.0667   1.0000
  15.500   1.4501   0.07018   0.06411  -0.0478   0.0643   1.0000
  15.750   1.4508   0.07306   0.06705  -0.0478   0.0613   1.0000
  16.000   1.4497   0.07614   0.07016  -0.0478   0.0579   1.0000
  16.250   1.4492   0.07923   0.07330  -0.0479   0.0546   1.0000
  16.500   1.4477   0.08240   0.07649  -0.0480   0.0502   1.0000
  16.750   1.4454   0.08573   0.07984  -0.0482   0.0455   1.0000
  17.000   1.4419   0.08922   0.08333  -0.0484   0.0398   1.0000
  17.250   1.4364   0.09303   0.08715  -0.0488   0.0339   1.0000
  17.500   1.4305   0.09689   0.09100  -0.0492   0.0280   1.0000
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