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EPPLER STE 871-514 AIRFOIL (ste87151-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER STE 871-514 AIRFOIL (ste87151-il)
Reynolds number: 100,000
Max Cl/Cd: 40.6 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ste87151-il-100000.txt
Download as CSV file: xf-ste87151-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER STE 871-514 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.6165   0.09824   0.09391  -0.0303   1.0020   0.1110
  -8.000  -0.6509   0.09483   0.09048  -0.0293   1.0020   0.1115
  -7.750  -0.6929   0.09119   0.08662  -0.0289   1.0020   0.1123
  -7.500  -0.6617   0.08768   0.08336  -0.0261   1.0020   0.1166
  -7.250  -0.6047   0.08309   0.07910  -0.0242   1.0020   0.1286
  -7.000  -0.6250   0.07925   0.07519  -0.0229   1.0020   0.1321
  -6.750  -0.6839   0.07695   0.07242  -0.0229   1.0020   0.1302
  -6.500  -0.6439   0.07126   0.06709  -0.0202   1.0020   0.1414
  -6.000  -0.6798   0.06667   0.06182  -0.0202   1.0020   0.1548
  -5.750  -0.6740   0.06347   0.05849  -0.0196   1.0020   0.1681
  -5.500  -0.6654   0.06058   0.05549  -0.0188   1.0020   0.1837
  -5.250  -0.6547   0.05787   0.05274  -0.0178   1.0020   0.2015
  -5.000  -0.6429   0.05534   0.05022  -0.0166   1.0020   0.2219
  -4.250  -0.5273   0.03692   0.02807  -0.0186   1.0020   0.0616
  -4.000  -0.5011   0.03486   0.02548  -0.0178   1.0020   0.0592
  -3.750  -0.4775   0.03354   0.02402  -0.0172   1.0020   0.0613
  -3.500  -0.4528   0.03226   0.02247  -0.0165   1.0020   0.0621
  -3.250  -0.4281   0.03106   0.02111  -0.0156   1.0020   0.0621
  -3.000  -0.4038   0.03011   0.02004  -0.0147   1.0020   0.0631
  -2.750  -0.3798   0.02925   0.01918  -0.0139   1.0020   0.0650
  -2.500  -0.3559   0.02864   0.01861  -0.0134   1.0020   0.0700
  -2.250  -0.3314   0.02805   0.01814  -0.0133   1.0020   0.0779
  -2.000  -0.3048   0.02748   0.01769  -0.0136   1.0020   0.0885
  -1.750  -0.2753   0.02684   0.01736  -0.0145   1.0020   0.1279
  -1.500  -0.1317   0.03227   0.02547  -0.0166   1.0020   0.9980
  -1.250  -0.1231   0.03218   0.02526  -0.0144   1.0020   0.9980
  -1.000  -0.1146   0.03213   0.02510  -0.0122   1.0020   0.9980
  -0.750  -0.1061   0.03210   0.02499  -0.0099   1.0020   0.9980
  -0.500  -0.0978   0.03211   0.02491  -0.0077   1.0020   0.9980
  -0.250  -0.0897   0.03213   0.02486  -0.0055   1.0020   0.9980
   0.000  -0.0817   0.03218   0.02483  -0.0032   1.0020   0.9980
   0.250  -0.0738   0.03225   0.02484  -0.0010   1.0020   0.9980
   0.500  -0.0661   0.03233   0.02487   0.0012   1.0020   0.9980
   0.750  -0.0585   0.03243   0.02492   0.0034   1.0020   0.9980
   1.000  -0.0510   0.03254   0.02499   0.0056   1.0020   0.9980
   1.250  -0.0436   0.03266   0.02508   0.0078   1.0020   0.9980
   1.500  -0.0197   0.03333   0.02570   0.0066   0.9979   0.9980
   1.750   0.0326   0.03487   0.02718   0.0002   0.9834   0.9980
   2.000   0.1483   0.03655   0.02874  -0.0166   0.9346   0.9980
   2.250   0.1885   0.03694   0.02911  -0.0196   0.9171   0.9980
   2.500   0.2249   0.03731   0.02948  -0.0219   0.9036   0.9980
   2.750   0.2579   0.03754   0.02972  -0.0236   0.8911   0.9980
   3.000   0.2820   0.03754   0.02974  -0.0235   0.8769   0.9980
   3.250   0.3059   0.03755   0.02977  -0.0235   0.8633   0.9980
   3.500   0.3336   0.03756   0.02982  -0.0239   0.8509   0.9980
   3.750   0.3787   0.03760   0.02991  -0.0272   0.8425   0.9980
   4.000   0.3997   0.03730   0.02968  -0.0263   0.8284   0.9980
   4.250   0.4238   0.03696   0.02940  -0.0258   0.8150   0.9980
   4.500   0.4519   0.03651   0.02903  -0.0259   0.8022   0.9980
   4.750   0.4876   0.03583   0.02842  -0.0269   0.7906   0.9980
   5.000   0.5389   0.03460   0.02734  -0.0298   0.7809   0.9980
   5.250   0.5705   0.03337   0.02621  -0.0295   0.7663   0.9980
   5.500   0.6054   0.03182   0.02478  -0.0294   0.7512   0.9980
   5.750   0.6404   0.03011   0.02320  -0.0290   0.7357   0.9980
   6.000   0.6741   0.02836   0.02162  -0.0283   0.7198   0.9980
   6.250   0.7054   0.02661   0.02001  -0.0271   0.7029   0.9980
   6.500   0.7388   0.02481   0.01835  -0.0262   0.6822   0.9980
   6.750   0.7722   0.02324   0.01689  -0.0254   0.6500   0.9980
   7.000   0.8238   0.02122   0.01474  -0.0268   0.5825   0.9980
   7.250   0.8530   0.02101   0.01370  -0.0255   0.4408   0.9980
   7.500   0.8493   0.02242   0.01431  -0.0207   0.3271   0.9980
   7.750   0.8490   0.02413   0.01531  -0.0170   0.2489   0.9980
   8.000   0.8597   0.02556   0.01637  -0.0150   0.2050   0.9980
   8.250   0.8774   0.02684   0.01736  -0.0141   0.1805   0.9980
   8.500   0.9012   0.02797   0.01839  -0.0140   0.1632   0.9980
   8.750   0.9302   0.02912   0.01943  -0.0147   0.1503   0.9980
   9.000   0.9654   0.03036   0.02054  -0.0164   0.1399   0.9980
   9.250   1.0013   0.03160   0.02179  -0.0182   0.1315   0.9980
   9.500   1.0401   0.03309   0.02339  -0.0203   0.1245   0.9980
   9.750   1.0898   0.03504   0.02527  -0.0245   0.1183   0.9980
  10.000   1.1192   0.03668   0.02723  -0.0253   0.1138   0.9980
  10.250   1.1699   0.03922   0.02971  -0.0300   0.1090   0.9980
  10.500   1.1857   0.04106   0.03205  -0.0285   0.1066   0.9980
  10.750   1.2059   0.04314   0.03446  -0.0281   0.1037   0.9980
  11.000   1.2412   0.04570   0.03710  -0.0303   0.1007   0.9980
  11.250   1.2540   0.04849   0.04027  -0.0289   0.0989   0.9980
  11.500   1.2531   0.05094   0.04322  -0.0254   0.0976   0.9980
  11.750   1.2521   0.05368   0.04638  -0.0222   0.0964   0.9980
  12.000   1.2491   0.05663   0.04971  -0.0190   0.0954   0.9980
  12.250   1.2443   0.05955   0.05294  -0.0158   0.0944   0.9980
  12.500   1.2776   0.06269   0.05601  -0.0181   0.0912   0.9980
  12.750   1.2572   0.06585   0.05955  -0.0133   0.0911   0.9980
  13.000   1.2366   0.06934   0.06336  -0.0091   0.0910   0.9980
  13.250   1.2137   0.07306   0.06739  -0.0054   0.0911   0.9980
  13.500   1.1898   0.07713   0.07172  -0.0023   0.0911   0.9980
  13.750   1.1664   0.08157   0.07639   0.0001   0.0913   0.9980
  14.000   1.1442   0.08637   0.08139   0.0016   0.0915   0.9980
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