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GOE 257 AIRFOIL (goe257-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 257 AIRFOIL (goe257-il)
Reynolds number: 500,000
Max Cl/Cd: 95.99 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe257-il-500000.txt
Download as CSV file: xf-goe257-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 257 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4022   0.09628   0.09414  -0.0131   1.0000   0.0176
  -8.000  -0.3981   0.09289   0.09077  -0.0149   1.0000   0.0180
  -7.750  -0.3957   0.08951   0.08742  -0.0168   1.0000   0.0186
  -7.500  -0.3891   0.08547   0.08340  -0.0223   1.0000   0.0195
  -7.250  -0.3750   0.08033   0.07825  -0.0314   1.0000   0.0198
  -7.000  -0.3596   0.07530   0.07319  -0.0376   1.0000   0.0199
  -6.750  -0.3449   0.07063   0.06847  -0.0418   1.0000   0.0199
  -6.500  -0.3317   0.06624   0.06403  -0.0446   0.9999   0.0199
  -6.250  -0.3138   0.05999   0.05776  -0.0488   0.9953   0.0204
  -6.000  -0.2889   0.05702   0.05476  -0.0518   0.9877   0.0210
  -5.750  -0.2590   0.05323   0.05088  -0.0565   0.9775   0.0219
  -5.500  -0.2274   0.04894   0.04644  -0.0613   0.9631   0.0234
  -5.250  -0.1841   0.04408   0.04115  -0.0659   0.9449   0.0256
  -5.000  -0.1592   0.04039   0.03714  -0.0667   0.9229   0.0257
  -4.750  -0.1439   0.03483   0.03142  -0.0677   0.8983   0.0266
  -4.500  -0.1232   0.03303   0.02946  -0.0676   0.8670   0.0273
  -4.250  -0.0996   0.03112   0.02728  -0.0677   0.8293   0.0283
  -4.000  -0.0733   0.02906   0.02487  -0.0678   0.7953   0.0301
  -3.750  -0.0402   0.02865   0.02392  -0.0672   0.7718   0.0331
  -3.500  -0.0141   0.02375   0.01862  -0.0686   0.7570   0.0348
  -3.250   0.0128   0.02243   0.01716  -0.0691   0.7443   0.0360
  -3.000   0.0410   0.02127   0.01578  -0.0695   0.7340   0.0381
  -2.750   0.0711   0.02107   0.01530  -0.0694   0.7246   0.0423
  -2.500   0.1001   0.01858   0.01248  -0.0702   0.7167   0.0456
  -2.250   0.1281   0.01779   0.01161  -0.0706   0.7087   0.0484
  -2.000   0.1577   0.01899   0.01263  -0.0703   0.7008   0.0550
  -1.750   0.1858   0.01626   0.00978  -0.0713   0.6941   0.0609
  -1.500   0.2146   0.01566   0.00905  -0.0717   0.6874   0.0722
  -1.250   0.2432   0.01520   0.00848  -0.0721   0.6803   0.0856
  -1.000   0.2715   0.01456   0.00782  -0.0726   0.6729   0.1009
  -0.500   0.3338   0.01206   0.00483  -0.0713   0.6573   0.0463
  -0.250   0.3628   0.01201   0.00469  -0.0713   0.6491   0.0437
   0.000   0.3916   0.01149   0.00418  -0.0715   0.6409   0.0424
   0.250   0.4203   0.01111   0.00374  -0.0716   0.6327   0.0420
   0.500   0.4493   0.01081   0.00344  -0.0718   0.6232   0.0422
   0.750   0.4782   0.01062   0.00322  -0.0720   0.6145   0.0425
   1.000   0.5070   0.01048   0.00304  -0.0722   0.6053   0.0429
   1.250   0.5360   0.01033   0.00288  -0.0725   0.5952   0.0441
   1.500   0.5648   0.01025   0.00275  -0.0727   0.5842   0.0460
   1.750   0.5935   0.01023   0.00267  -0.0729   0.5723   0.0473
   2.000   0.6221   0.01022   0.00263  -0.0730   0.5592   0.0502
   2.250   0.6501   0.00906   0.00277  -0.0739   0.5459   0.6136
   2.500   0.6743   0.00810   0.00265  -0.0729   0.5305   1.0000
   2.750   0.7026   0.00823   0.00267  -0.0730   0.5113   1.0000
   3.000   0.7308   0.00839   0.00273  -0.0732   0.4949   1.0000
   3.250   0.7589   0.00855   0.00282  -0.0734   0.4816   1.0000
   3.500   0.7870   0.00873   0.00294  -0.0735   0.4691   1.0000
   3.750   0.8150   0.00892   0.00307  -0.0737   0.4565   1.0000
   4.000   0.8428   0.00913   0.00321  -0.0738   0.4442   1.0000
   4.250   0.8708   0.00930   0.00337  -0.0740   0.4324   1.0000
   4.500   0.8987   0.00950   0.00353  -0.0742   0.4193   1.0000
   4.750   0.9261   0.00975   0.00371  -0.0743   0.4008   1.0000
   5.000   0.9537   0.00997   0.00388  -0.0744   0.3795   1.0000
   5.250   0.9810   0.01022   0.00408  -0.0745   0.3571   1.0000
   5.500   1.0075   0.01062   0.00431  -0.0746   0.3118   1.0000
   5.750   1.0315   0.01146   0.00477  -0.0745   0.2452   1.0000
   6.000   1.0570   0.01202   0.00518  -0.0744   0.2183   1.0000
   6.250   1.0829   0.01248   0.00558  -0.0744   0.1982   1.0000
   6.500   1.1084   0.01298   0.00597  -0.0743   0.1721   1.0000
   6.750   1.1262   0.01470   0.00702  -0.0735   0.0593   1.0000
   7.250   1.1727   0.01626   0.00841  -0.0725   0.0208   1.0000
   7.500   1.1967   0.01686   0.00911  -0.0720   0.0192   1.0000
   7.750   1.2194   0.01759   0.00992  -0.0714   0.0176   1.0000
   8.000   1.2397   0.01859   0.01101  -0.0704   0.0160   1.0000
   8.250   1.2584   0.01970   0.01226  -0.0692   0.0152   1.0000
   8.500   1.2781   0.02058   0.01326  -0.0681   0.0147   1.0000
   8.750   1.2958   0.02160   0.01437  -0.0667   0.0143   1.0000
   9.000   1.3115   0.02272   0.01560  -0.0651   0.0138   1.0000
   9.250   1.3251   0.02395   0.01692  -0.0632   0.0134   1.0000
   9.500   1.3365   0.02525   0.01832  -0.0609   0.0130   1.0000
   9.750   1.3463   0.02657   0.01974  -0.0585   0.0126   1.0000
  10.000   1.3538   0.02796   0.02120  -0.0558   0.0122   1.0000
  10.250   1.3554   0.02956   0.02286  -0.0524   0.0118   1.0000
  10.500   1.3551   0.03174   0.02509  -0.0489   0.0114   1.0000
  10.750   1.3601   0.03417   0.02761  -0.0463   0.0112   1.0000
  11.000   1.3733   0.03695   0.03050  -0.0447   0.0111   1.0000
  11.250   1.3812   0.03889   0.03259  -0.0427   0.0109   1.0000
  11.500   1.3865   0.04066   0.03453  -0.0406   0.0108   1.0000
  11.750   1.3913   0.04271   0.03677  -0.0387   0.0107   1.0000
  12.000   1.3955   0.04515   0.03938  -0.0370   0.0107   1.0000
  12.250   1.3975   0.04792   0.04235  -0.0352   0.0107   1.0000
  12.500   1.3970   0.05115   0.04579  -0.0336   0.0107   1.0000
  12.750   1.4128   0.05461   0.04934  -0.0324   0.0112   1.0000
  13.000   1.4079   0.05698   0.05190  -0.0311   0.0114   1.0000
  13.250   1.2560   0.05645   0.05173  -0.0182   0.0112   1.0000
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