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GOE 397 AIRFOIL (goe397-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 397 AIRFOIL (goe397-il)
Reynolds number: 100,000
Max Cl/Cd: 60.98 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe397-il-100000-n5.txt
Download as CSV file: xf-goe397-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 397 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3737   0.09415   0.08927  -0.0204   1.0000   0.0314
  -7.500  -0.3712   0.09150   0.08668  -0.0210   1.0000   0.0318
  -7.250  -0.3692   0.08887   0.08412  -0.0217   1.0000   0.0325
  -7.000  -0.3644   0.08598   0.08129  -0.0232   1.0000   0.0334
  -6.750  -0.3585   0.08306   0.07842  -0.0250   1.0000   0.0343
  -6.500  -0.3511   0.08011   0.07551  -0.0274   1.0000   0.0356
  -6.250  -0.3369   0.07767   0.07309  -0.0337   1.0000   0.0379
  -6.000  -0.3218   0.07471   0.07011  -0.0380   1.0000   0.0384
  -5.750  -0.3063   0.07155   0.06689  -0.0413   1.0000   0.0387
  -5.250  -0.3016   0.06389   0.05939  -0.0383   1.0000   0.0409
  -5.000  -0.2971   0.06153   0.05706  -0.0367   1.0000   0.0431
  -4.750  -0.2614   0.05713   0.05252  -0.0433   0.9923   0.0465
  -4.250  -0.1840   0.04809   0.04307  -0.0564   0.9765   0.0570
  -4.000  -0.1405   0.04293   0.03752  -0.0623   0.9681   0.0496
  -3.750  -0.1047   0.03819   0.03248  -0.0662   0.9598   0.0446
  -3.500  -0.0644   0.03451   0.02838  -0.0701   0.9535   0.0486
  -3.250  -0.0300   0.03099   0.02443  -0.0723   0.9445   0.0484
  -3.000   0.0066   0.02782   0.02074  -0.0745   0.9377   0.0489
  -2.750   0.0420   0.02592   0.01813  -0.0756   0.9287   0.0522
  -2.500   0.0741   0.02359   0.01543  -0.0767   0.9202   0.0518
  -2.250   0.1079   0.02179   0.01321  -0.0778   0.9126   0.0519
  -2.000   0.1387   0.02045   0.01152  -0.0783   0.9032   0.0523
  -1.750   0.1710   0.01893   0.00972  -0.0792   0.8957   0.0534
  -1.500   0.2010   0.01816   0.00889  -0.0798   0.8862   0.0581
  -1.250   0.2313   0.01746   0.00802  -0.0801   0.8770   0.0607
  -1.000   0.2627   0.01667   0.00707  -0.0805   0.8693   0.0605
  -0.750   0.2909   0.01608   0.00639  -0.0804   0.8594   0.0604
  -0.500   0.3192   0.01557   0.00584  -0.0803   0.8502   0.0606
   0.000   0.3753   0.01486   0.00497  -0.0798   0.8303   0.0619
   0.250   0.4023   0.01463   0.00464  -0.0793   0.8173   0.0631
   0.500   0.4294   0.01447   0.00437  -0.0787   0.8042   0.0652
   0.750   0.4566   0.01433   0.00420  -0.0783   0.7926   0.0698
   1.000   0.4840   0.01421   0.00410  -0.0780   0.7826   0.0848
   1.250   0.5273   0.01215   0.00409  -0.0815   0.7735   1.0000
   1.500   0.5530   0.01229   0.00413  -0.0809   0.7630   1.0000
   1.750   0.5790   0.01243   0.00418  -0.0803   0.7533   1.0000
   2.000   0.6049   0.01257   0.00426  -0.0797   0.7437   1.0000
   2.250   0.6304   0.01273   0.00441  -0.0791   0.7330   1.0000
   2.500   0.6560   0.01289   0.00459  -0.0785   0.7230   1.0000
   2.750   0.6819   0.01304   0.00474  -0.0779   0.7133   1.0000
   3.000   0.7073   0.01320   0.00495  -0.0773   0.7024   1.0000
   3.250   0.7327   0.01338   0.00522  -0.0767   0.6913   1.0000
   3.500   0.7581   0.01355   0.00545  -0.0760   0.6795   1.0000
   3.750   0.7829   0.01370   0.00566  -0.0750   0.6638   1.0000
   4.000   0.8070   0.01382   0.00577  -0.0738   0.6421   1.0000
   4.250   0.8297   0.01395   0.00594  -0.0723   0.6110   1.0000
   4.500   0.8517   0.01412   0.00609  -0.0707   0.5729   1.0000
   4.750   0.8739   0.01433   0.00634  -0.0693   0.5303   1.0000
   5.000   0.8943   0.01468   0.00652  -0.0675   0.4625   1.0000
   5.250   0.9116   0.01547   0.00693  -0.0654   0.3806   1.0000
   5.500   0.9262   0.01675   0.00767  -0.0633   0.2567   1.0000
   5.750   0.9350   0.01903   0.00898  -0.0610   0.1154   1.0000
   6.000   0.9518   0.02038   0.01011  -0.0595   0.0801   1.0000
   6.250   0.9695   0.02157   0.01130  -0.0581   0.0613   1.0000
   6.500   0.9861   0.02289   0.01270  -0.0564   0.0465   1.0000
   6.750   1.0016   0.02429   0.01422  -0.0546   0.0372   1.0000
   7.000   1.0181   0.02557   0.01555  -0.0529   0.0312   1.0000
   7.250   1.0338   0.02728   0.01740  -0.0510   0.0281   1.0000
   7.500   1.0523   0.02881   0.01908  -0.0495   0.0245   1.0000
   7.750   1.0700   0.03039   0.02072  -0.0482   0.0218   1.0000
   8.000   1.0892   0.03323   0.02369  -0.0470   0.0204   1.0000
   8.250   1.1105   0.03595   0.02675  -0.0457   0.0197   1.0000
   8.500   1.1292   0.03886   0.03018  -0.0443   0.0185   1.0000
   8.750   1.1439   0.04189   0.03368  -0.0425   0.0171   1.0000
   9.000   1.1545   0.04535   0.03760  -0.0405   0.0163   1.0000
   9.250   1.1601   0.04920   0.04193  -0.0382   0.0161   1.0000
   9.500   1.1607   0.05320   0.04638  -0.0357   0.0159   1.0000
   9.750   1.1565   0.05721   0.05078  -0.0332   0.0159   1.0000
  10.000   1.1474   0.06109   0.05499  -0.0306   0.0159   1.0000
  10.250   1.1328   0.06470   0.05887  -0.0278   0.0159   1.0000
  10.500   1.1160   0.06854   0.06294  -0.0260   0.0160   1.0000
  10.750   1.0978   0.07287   0.06747  -0.0256   0.0160   1.0000
  11.000   1.0788   0.07778   0.07257  -0.0265   0.0161   1.0000
  11.250   1.0591   0.08344   0.07839  -0.0287   0.0163   1.0000
  11.500   1.0389   0.09005   0.08515  -0.0323   0.0164   1.0000
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