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S8055 (12%) (s8055-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S8055 (12%) (s8055-il)
Reynolds number: 100,000
Max Cl/Cd: 48.31 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s8055-il-100000-n5.txt
Download as CSV file: xf-s8055-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S8055 (12%)                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.4493   0.10006   0.09489  -0.0394   1.0000   0.0251
 -10.750  -0.4493   0.09583   0.09070  -0.0412   1.0000   0.0249
 -10.500  -0.4508   0.09134   0.08627  -0.0432   1.0000   0.0246
 -10.250  -0.4549   0.08625   0.08123  -0.0458   1.0000   0.0243
 -10.000  -0.4639   0.07974   0.07478  -0.0496   1.0000   0.0240
  -9.750  -0.4821   0.07055   0.06563  -0.0564   1.0000   0.0234
  -9.500  -0.5064   0.06405   0.05909  -0.0609   1.0000   0.0230
  -9.250  -0.5349   0.06013   0.05513  -0.0607   1.0000   0.0228
  -9.000  -0.5668   0.05861   0.05361  -0.0557   1.0000   0.0226
  -8.750  -0.5979   0.05705   0.05199  -0.0500   1.0000   0.0225
  -8.500  -0.6030   0.05154   0.04608  -0.0519   0.9900   0.0223
  -8.250  -0.5984   0.04659   0.04064  -0.0533   0.9818   0.0220
  -8.000  -0.5891   0.04236   0.03589  -0.0537   0.9746   0.0221
  -7.750  -0.5746   0.03884   0.03187  -0.0539   0.9688   0.0221
  -7.500  -0.5569   0.03592   0.02848  -0.0538   0.9631   0.0224
  -7.250  -0.5327   0.03325   0.02535  -0.0544   0.9594   0.0228
  -7.000  -0.5105   0.03109   0.02282  -0.0541   0.9547   0.0233
  -6.750  -0.4864   0.02915   0.02053  -0.0539   0.9501   0.0241
  -6.500  -0.4578   0.02747   0.01850  -0.0543   0.9467   0.0253
  -6.250  -0.4285   0.02626   0.01727  -0.0554   0.9439   0.0272
  -6.000  -0.4070   0.02531   0.01618  -0.0545   0.9383   0.0292
  -5.750  -0.3813   0.02412   0.01483  -0.0543   0.9340   0.0313
  -5.500  -0.3538   0.02305   0.01376  -0.0547   0.9306   0.0337
  -5.250  -0.3284   0.02222   0.01278  -0.0544   0.9264   0.0375
  -5.000  -0.3080   0.02150   0.01207  -0.0534   0.9206   0.0433
  -4.750  -0.2816   0.02070   0.01124  -0.0533   0.9165   0.0548
  -4.500  -0.2533   0.01982   0.01047  -0.0537   0.9133   0.0768
  -4.250  -0.2368   0.01916   0.01001  -0.0519   0.9065   0.1122
  -4.000  -0.2130   0.01838   0.00958  -0.0516   0.9019   0.1814
  -3.750  -0.1867   0.01759   0.00922  -0.0517   0.8984   0.2776
  -3.500  -0.1712   0.01707   0.00907  -0.0497   0.8916   0.3670
  -3.250  -0.1502   0.01647   0.00893  -0.0484   0.8866   0.4769
  -3.000  -0.1252   0.01604   0.00897  -0.0472   0.8831   0.5944
  -2.750  -0.1066   0.01605   0.00919  -0.0447   0.8766   0.6751
  -2.500  -0.0820   0.01612   0.00927  -0.0433   0.8716   0.7306
  -2.250  -0.0532   0.01617   0.00927  -0.0426   0.8678   0.7705
  -2.000  -0.0328   0.01631   0.00935  -0.0407   0.8611   0.8004
  -1.750  -0.0054   0.01640   0.00937  -0.0398   0.8559   0.8248
  -1.500   0.0250   0.01642   0.00929  -0.0396   0.8520   0.8473
  -1.250   0.0502   0.01655   0.00936  -0.0386   0.8453   0.8658
  -1.000   0.0820   0.01660   0.00933  -0.0388   0.8400   0.8824
  -0.750   0.1186   0.01659   0.00923  -0.0399   0.8364   0.8972
  -0.500   0.1486   0.01669   0.00927  -0.0401   0.8293   0.9113
  -0.250   0.1886   0.01669   0.00919  -0.0421   0.8240   0.9223
   0.000   0.2311   0.01658   0.00900  -0.0445   0.8200   0.9314
   0.250   0.2631   0.01664   0.00903  -0.0454   0.8111   0.9426
   0.500   0.3080   0.01648   0.00881  -0.0484   0.8056   0.9489
   0.750   0.3430   0.01645   0.00875  -0.0498   0.7968   0.9579
   1.000   0.3848   0.01622   0.00849  -0.0523   0.7896   0.9636
   1.250   0.4180   0.01613   0.00839  -0.0534   0.7787   0.9720
   1.500   0.4560   0.01589   0.00813  -0.0552   0.7688   0.9781
   1.750   0.4908   0.01567   0.00789  -0.0565   0.7579   0.9850
   2.000   0.5253   0.01549   0.00774  -0.0579   0.7442   0.9917
   2.250   0.5598   0.01530   0.00756  -0.0592   0.7298   0.9984
   2.500   0.5811   0.01519   0.00745  -0.0580   0.7146   1.0000
   2.750   0.5982   0.01509   0.00736  -0.0559   0.6987   1.0000
   3.000   0.6160   0.01498   0.00723  -0.0539   0.6819   1.0000
   3.250   0.6332   0.01492   0.00714  -0.0517   0.6629   1.0000
   3.500   0.6509   0.01488   0.00707  -0.0497   0.6423   1.0000
   3.750   0.6703   0.01485   0.00697  -0.0478   0.6203   1.0000
   4.000   0.6886   0.01491   0.00697  -0.0458   0.5955   1.0000
   4.250   0.7076   0.01502   0.00697  -0.0440   0.5692   1.0000
   4.500   0.7262   0.01520   0.00702  -0.0421   0.5407   1.0000
   4.750   0.7442   0.01545   0.00716  -0.0402   0.5102   1.0000
   5.000   0.7618   0.01577   0.00734  -0.0382   0.4790   1.0000
   5.250   0.7790   0.01615   0.00758  -0.0363   0.4464   1.0000
   5.500   0.7959   0.01659   0.00787  -0.0344   0.4141   1.0000
   5.750   0.8125   0.01708   0.00822  -0.0325   0.3827   1.0000
   6.000   0.8290   0.01762   0.00861  -0.0306   0.3533   1.0000
   6.500   0.8622   0.01876   0.00953  -0.0272   0.3014   1.0000
   6.750   0.8787   0.01937   0.01003  -0.0255   0.2800   1.0000
   7.000   0.8960   0.01996   0.01056  -0.0240   0.2606   1.0000
   7.250   0.9131   0.02057   0.01113  -0.0225   0.2436   1.0000
   7.500   0.9301   0.02119   0.01173  -0.0210   0.2279   1.0000
   7.750   0.9468   0.02184   0.01235  -0.0195   0.2140   1.0000
   8.000   0.9631   0.02250   0.01299  -0.0180   0.2009   1.0000
   8.250   0.9786   0.02321   0.01366  -0.0164   0.1889   1.0000
   8.500   0.9941   0.02387   0.01438  -0.0148   0.1772   1.0000
   8.750   1.0087   0.02457   0.01511  -0.0130   0.1659   1.0000
   9.000   1.0224   0.02532   0.01587  -0.0113   0.1563   1.0000
   9.250   1.0350   0.02614   0.01669  -0.0094   0.1470   1.0000
   9.500   1.0494   0.02694   0.01758  -0.0079   0.1375   1.0000
   9.750   1.0616   0.02786   0.01851  -0.0062   0.1296   1.0000
  10.000   1.0746   0.02877   0.01950  -0.0047   0.1215   1.0000
  10.250   1.0867   0.02978   0.02056  -0.0031   0.1144   1.0000
  10.500   1.0983   0.03082   0.02167  -0.0016   0.1078   1.0000
  10.750   1.1096   0.03196   0.02287  -0.0002   0.1020   1.0000
  11.000   1.1208   0.03310   0.02412   0.0012   0.0962   1.0000
  11.250   1.1293   0.03442   0.02542   0.0027   0.0920   1.0000
  11.500   1.1412   0.03571   0.02689   0.0039   0.0873   1.0000
  11.750   1.1504   0.03707   0.02835   0.0052   0.0835   1.0000
  12.250   1.1676   0.04016   0.03165   0.0076   0.0767   1.0000
  12.500   1.1755   0.04178   0.03341   0.0087   0.0736   1.0000
  12.750   1.1823   0.04348   0.03520   0.0097   0.0711   1.0000
  13.000   1.1895   0.04529   0.03702   0.0107   0.0691   1.0000
  13.250   1.1957   0.04733   0.03929   0.0116   0.0669   1.0000
  13.500   1.1997   0.04950   0.04169   0.0124   0.0646   1.0000
  13.750   1.2028   0.05176   0.04411   0.0131   0.0626   1.0000
  14.000   1.2049   0.05406   0.04655   0.0136   0.0608   1.0000
  14.250   1.2081   0.05641   0.04898   0.0140   0.0594   1.0000
  14.500   1.2117   0.05893   0.05156   0.0143   0.0580   1.0000
  14.750   1.2054   0.06244   0.05538   0.0142   0.0568   1.0000
  15.000   1.1972   0.06631   0.05954   0.0138   0.0556   1.0000
  15.250   1.1876   0.07053   0.06400   0.0129   0.0545   1.0000
  15.500   1.1761   0.07516   0.06886   0.0115   0.0535   1.0000
  15.750   1.1634   0.08022   0.07413   0.0096   0.0526   1.0000
  16.000   1.1491   0.08585   0.07995   0.0072   0.0518   1.0000
  16.250   1.1327   0.09213   0.08642   0.0041   0.0512   1.0000
  16.500   1.1107   0.09985   0.09434  -0.0001   0.0508   1.0000
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