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GOE 517 AIRFOIL (goe517-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 517 AIRFOIL (goe517-il)
Reynolds number: 50,000
Max Cl/Cd: 37.39 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe517-il-50000.txt
Download as CSV file: xf-goe517-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 517 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3640   0.10990   0.10292  -0.0209   1.0000   0.1336
  -8.500  -0.3710   0.10904   0.10219  -0.0227   1.0000   0.1367
  -8.250  -0.3849   0.10907   0.10238  -0.0245   1.0000   0.1376
  -8.000  -0.3567   0.10134   0.09459  -0.0219   1.0000   0.1446
  -7.750  -0.3603   0.09953   0.09289  -0.0223   1.0000   0.1494
  -7.500  -0.3744   0.09918   0.09272  -0.0241   1.0000   0.1517
  -7.250  -0.3604   0.09395   0.08752  -0.0215   1.0000   0.1579
  -7.000  -0.3629   0.09200   0.08566  -0.0222   1.0000   0.1640
  -6.750  -0.3752   0.09206   0.08584  -0.0269   1.0000   0.1667
  -6.500  -0.3597   0.08623   0.08008  -0.0215   1.0000   0.1756
  -6.250  -0.3692   0.08614   0.08005  -0.0262   1.0000   0.1811
  -6.000  -0.3586   0.08097   0.07499  -0.0211   1.0000   0.1882
  -5.750  -0.3641   0.08025   0.07430  -0.0249   1.0000   0.1960
  -5.500  -0.3570   0.07593   0.07008  -0.0202   1.0000   0.2031
  -5.250  -0.3575   0.07366   0.06782  -0.0209   1.0000   0.2125
  -5.000  -0.3553   0.07202   0.06616  -0.0221   1.0000   0.2250
  -4.750  -0.3514   0.06855   0.06278  -0.0184   1.0000   0.2358
  -4.500  -0.3470   0.06679   0.06096  -0.0200   1.0000   0.2536
  -4.250  -0.3430   0.06352   0.05776  -0.0175   1.0000   0.2692
  -4.000  -0.3399   0.06051   0.05484  -0.0139   1.0000   0.2898
  -3.750  -0.3368   0.05802   0.05240  -0.0114   1.0000   0.3198
  -3.500  -0.3368   0.05547   0.04994  -0.0074   1.0000   0.3607
  -3.250  -0.3387   0.05305   0.04764  -0.0021   1.0000   0.4082
  -3.000  -0.3419   0.05061   0.04531   0.0035   1.0000   0.4601
  -2.750  -0.3428   0.04808   0.04286   0.0090   1.0000   0.5042
  -2.500  -0.3404   0.04556   0.04043   0.0135   1.0000   0.5429
  -2.250  -0.3312   0.04300   0.03787   0.0152   1.0000   0.5743
  -2.000  -0.3155   0.04021   0.03508   0.0154   1.0000   0.5929
  -1.750  -0.1156   0.03595   0.02747  -0.0324   1.0000   0.1792
  -1.500  -0.0872   0.03402   0.02489  -0.0326   1.0000   0.1663
  -1.250  -0.0672   0.03236   0.02313  -0.0322   1.0000   0.1727
  -1.000  -0.0439   0.03102   0.02137  -0.0318   1.0000   0.1726
  -0.750  -0.0214   0.03001   0.01997  -0.0314   1.0000   0.1781
  -0.500  -0.0007   0.02921   0.01896  -0.0310   1.0000   0.1917
  -0.250   0.0195   0.02848   0.01803  -0.0304   1.0000   0.2033
   0.000   0.0431   0.02805   0.01736  -0.0305   0.9995   0.2270
   0.250   0.1009   0.02755   0.01670  -0.0364   0.9873   0.2736
   0.500   0.1557   0.02708   0.01641  -0.0419   0.9735   0.3393
   0.750   0.2260   0.02531   0.01601  -0.0496   0.9584   1.0000
   1.000   0.2786   0.02615   0.01628  -0.0546   0.9391   1.0000
   1.250   0.3245   0.02684   0.01667  -0.0585   0.9199   1.0000
   1.500   0.3719   0.02745   0.01708  -0.0625   0.9021   1.0000
   1.750   0.4197   0.02797   0.01745  -0.0664   0.8853   1.0000
   2.000   0.4590   0.02843   0.01784  -0.0686   0.8671   1.0000
   2.250   0.4975   0.02884   0.01821  -0.0705   0.8485   1.0000
   2.500   0.5431   0.02904   0.01839  -0.0732   0.8307   1.0000
   2.750   0.5926   0.02900   0.01838  -0.0762   0.8135   1.0000
   3.000   0.6319   0.02905   0.01849  -0.0773   0.7951   1.0000
   3.250   0.6631   0.02924   0.01873  -0.0771   0.7746   1.0000
   3.500   0.7030   0.02903   0.01859  -0.0777   0.7560   1.0000
   3.750   0.7354   0.02901   0.01868  -0.0772   0.7359   1.0000
   4.000   0.7646   0.02909   0.01882  -0.0762   0.7149   1.0000
   4.250   0.8008   0.02875   0.01855  -0.0757   0.6964   1.0000
   4.500   0.8226   0.02921   0.01909  -0.0740   0.6744   1.0000
   4.750   0.8528   0.02922   0.01923  -0.0730   0.6556   1.0000
   5.000   0.8835   0.02924   0.01930  -0.0720   0.6379   1.0000
   5.250   0.9023   0.03014   0.02032  -0.0704   0.6182   1.0000
   5.500   0.9269   0.03072   0.02101  -0.0692   0.6010   1.0000
   5.750   0.9515   0.03138   0.02183  -0.0681   0.5849   1.0000
   6.000   0.9751   0.03221   0.02279  -0.0670   0.5696   1.0000
   6.250   0.9973   0.03319   0.02393  -0.0658   0.5548   1.0000
   6.500   1.0174   0.03440   0.02532  -0.0646   0.5405   1.0000
   6.750   1.0365   0.03570   0.02687  -0.0633   0.5263   1.0000
   7.000   1.0551   0.03702   0.02842  -0.0619   0.5120   1.0000
   7.250   1.0827   0.03680   0.02834  -0.0598   0.4907   1.0000
   7.500   1.1096   0.03558   0.02719  -0.0569   0.4603   1.0000
   7.750   1.1337   0.03422   0.02594  -0.0537   0.4270   1.0000
   8.000   1.1535   0.03196   0.02357  -0.0494   0.3824   1.0000
   8.250   1.1612   0.03106   0.02255  -0.0445   0.3311   1.0000
   8.500   1.1520   0.03184   0.02295  -0.0381   0.2552   1.0000
   8.750   1.1409   0.03389   0.02438  -0.0326   0.1893   1.0000
   9.000   1.1429   0.03627   0.02627  -0.0291   0.1543   1.0000
   9.250   1.1532   0.03871   0.02857  -0.0267   0.1316   1.0000
   9.500   1.1740   0.04140   0.03107  -0.0254   0.1160   1.0000
   9.750   1.2006   0.04458   0.03449  -0.0248   0.1059   1.0000
  10.000   1.2219   0.04797   0.03802  -0.0240   0.0984   1.0000
  10.250   1.2375   0.05144   0.04187  -0.0225   0.0940   1.0000
  10.500   1.2521   0.05534   0.04608  -0.0212   0.0917   1.0000
  10.750   1.2650   0.05991   0.05087  -0.0202   0.0896   1.0000
  11.000   1.2654   0.06439   0.05568  -0.0182   0.0888   1.0000
  11.250   1.2546   0.06821   0.05992  -0.0155   0.0885   1.0000
  11.500   1.2395   0.07201   0.06405  -0.0128   0.0883   1.0000
  11.750   1.2226   0.07597   0.06826  -0.0105   0.0885   1.0000
  12.000   1.2035   0.08020   0.07271  -0.0090   0.0887   1.0000
  12.250   1.1848   0.08497   0.07765  -0.0085   0.0890   1.0000
  12.500   1.0852   0.09536   0.08856  -0.0159   0.0974   1.0000
  12.750   1.0563   0.10417   0.09741  -0.0209   0.0993   1.0000
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