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S6061 9% (s6061-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: S6061 9% (s6061-il)
Reynolds number: 200,000
Max Cl/Cd: 63.29 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s6061-il-200000-n5.txt
Download as CSV file: xf-s6061-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S6061 9%                                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5065   0.10345   0.09987  -0.0102   1.0000   0.0154
  -9.750  -0.5045   0.09954   0.09598  -0.0116   1.0000   0.0147
  -9.500  -0.5034   0.09532   0.09180  -0.0136   1.0000   0.0142
  -9.250  -0.5033   0.09090   0.08741  -0.0158   1.0000   0.0137
  -9.000  -0.5059   0.08588   0.08244  -0.0185   1.0000   0.0131
  -8.750  -0.5099   0.08060   0.07722  -0.0217   1.0000   0.0127
  -8.500  -0.5181   0.07435   0.07102  -0.0260   1.0000   0.0121
  -8.250  -0.5311   0.06722   0.06396  -0.0328   1.0000   0.0118
  -8.000  -0.5504   0.05394   0.05047  -0.0404   1.0000   0.0106
  -7.750  -0.5493   0.04947   0.04577  -0.0415   1.0000   0.0104
  -7.500  -0.5503   0.04485   0.04092  -0.0418   1.0000   0.0102
  -7.250  -0.5484   0.04036   0.03613  -0.0414   1.0000   0.0101
  -7.000  -0.5443   0.03633   0.03175  -0.0402   1.0000   0.0100
  -6.750  -0.5388   0.03281   0.02784  -0.0383   1.0000   0.0100
  -6.500  -0.5314   0.02986   0.02451  -0.0360   1.0000   0.0099
  -6.250  -0.5038   0.02634   0.02039  -0.0374   0.9930   0.0100
  -6.000  -0.4733   0.02356   0.01710  -0.0387   0.9866   0.0101
  -5.750  -0.4412   0.02142   0.01455  -0.0400   0.9810   0.0103
  -5.500  -0.4104   0.01940   0.01222  -0.0409   0.9743   0.0106
  -5.250  -0.3792   0.01767   0.01033  -0.0420   0.9685   0.0115
  -5.000  -0.3485   0.01683   0.00940  -0.0430   0.9610   0.0131
  -4.750  -0.3168   0.01584   0.00824  -0.0438   0.9545   0.0145
  -4.500  -0.2875   0.01493   0.00719  -0.0442   0.9462   0.0154
  -4.250  -0.2584   0.01413   0.00626  -0.0445   0.9380   0.0166
  -4.000  -0.2292   0.01347   0.00551  -0.0448   0.9300   0.0194
  -3.750  -0.2023   0.01288   0.00489  -0.0446   0.9204   0.0281
  -3.500  -0.1757   0.01221   0.00436  -0.0444   0.9116   0.0678
  -3.250  -0.1502   0.01158   0.00402  -0.0442   0.9024   0.1356
  -3.000  -0.1260   0.01091   0.00375  -0.0438   0.8924   0.2334
  -2.750  -0.1011   0.01042   0.00351  -0.0434   0.8831   0.3143
  -2.500  -0.0769   0.00991   0.00331  -0.0427   0.8738   0.4103
  -2.250  -0.0536   0.00943   0.00316  -0.0418   0.8634   0.5158
  -2.000  -0.0306   0.00905   0.00309  -0.0406   0.8538   0.6151
  -1.500   0.0168   0.00867   0.00301  -0.0379   0.8340   0.7501
  -1.250   0.0412   0.00859   0.00296  -0.0366   0.8238   0.7937
  -1.000   0.0659   0.00855   0.00290  -0.0354   0.8137   0.8290
  -0.750   0.0910   0.00852   0.00285  -0.0343   0.8031   0.8590
  -0.250   0.1457   0.00849   0.00273  -0.0332   0.7800   0.9091
   0.000   0.1768   0.00849   0.00267  -0.0335   0.7683   0.9306
   0.250   0.2117   0.00849   0.00260  -0.0347   0.7561   0.9490
   0.500   0.2483   0.00850   0.00253  -0.0364   0.7434   0.9650
   0.750   0.2858   0.00851   0.00247  -0.0384   0.7300   0.9786
   1.000   0.3241   0.00853   0.00241  -0.0406   0.7154   0.9902
   1.250   0.3601   0.00855   0.00238  -0.0424   0.7000   1.0000
   1.500   0.3832   0.00862   0.00238  -0.0415   0.6848   1.0000
   1.750   0.4066   0.00870   0.00239  -0.0406   0.6694   1.0000
   2.000   0.4304   0.00880   0.00243  -0.0398   0.6537   1.0000
   2.250   0.4545   0.00891   0.00249  -0.0391   0.6374   1.0000
   2.500   0.4789   0.00904   0.00256  -0.0384   0.6204   1.0000
   2.750   0.5036   0.00917   0.00265  -0.0378   0.6017   1.0000
   3.000   0.5284   0.00933   0.00275  -0.0371   0.5815   1.0000
   3.250   0.5534   0.00950   0.00289  -0.0366   0.5605   1.0000
   3.500   0.5784   0.00969   0.00302  -0.0360   0.5382   1.0000
   3.750   0.6034   0.00989   0.00318  -0.0355   0.5139   1.0000
   4.000   0.6282   0.01013   0.00336  -0.0349   0.4871   1.0000
   4.250   0.6528   0.01040   0.00359  -0.0344   0.4570   1.0000
   4.500   0.6771   0.01072   0.00382  -0.0338   0.4247   1.0000
   4.750   0.7013   0.01108   0.00409  -0.0332   0.3896   1.0000
   5.000   0.7240   0.01159   0.00440  -0.0325   0.3419   1.0000
   5.250   0.7449   0.01232   0.00481  -0.0317   0.2733   1.0000
   5.500   0.7659   0.01309   0.00526  -0.0310   0.2096   1.0000
   5.750   0.7887   0.01370   0.00572  -0.0304   0.1711   1.0000
   6.000   0.8104   0.01444   0.00626  -0.0298   0.1264   1.0000
   6.250   0.8319   0.01523   0.00686  -0.0291   0.0863   1.0000
   6.500   0.8526   0.01614   0.00758  -0.0283   0.0505   1.0000
   6.750   0.8734   0.01705   0.00841  -0.0274   0.0314   1.0000
   7.250   0.9164   0.01861   0.01015  -0.0258   0.0225   1.0000
   7.500   0.9377   0.01938   0.01102  -0.0250   0.0203   1.0000
   7.750   0.9575   0.02028   0.01203  -0.0240   0.0191   1.0000
   8.000   0.9753   0.02141   0.01327  -0.0228   0.0181   1.0000
   8.250   0.9912   0.02271   0.01468  -0.0214   0.0174   1.0000
   8.500   1.0085   0.02387   0.01598  -0.0201   0.0170   1.0000
   8.750   1.0252   0.02515   0.01744  -0.0187   0.0166   1.0000
   9.000   1.0418   0.02650   0.01893  -0.0174   0.0160   1.0000
   9.250   1.0586   0.02777   0.02035  -0.0162   0.0151   1.0000
   9.500   1.0743   0.02912   0.02185  -0.0149   0.0142   1.0000
   9.750   1.0890   0.03071   0.02360  -0.0136   0.0137   1.0000
  10.000   1.1023   0.03246   0.02553  -0.0122   0.0132   1.0000
  10.250   1.1138   0.03432   0.02757  -0.0107   0.0128   1.0000
  10.500   1.1218   0.03636   0.02979  -0.0088   0.0124   1.0000
  10.750   1.1258   0.03875   0.03238  -0.0068   0.0120   1.0000
  11.250   1.1188   0.04447   0.03868  -0.0025   0.0111   1.0000
  11.500   1.1159   0.04671   0.04119  -0.0010   0.0108   1.0000
  11.750   1.1093   0.04968   0.04443   0.0000   0.0105   1.0000
  12.000   1.1001   0.05321   0.04821   0.0004   0.0104   1.0000
  12.250   1.0882   0.05732   0.05257   0.0000   0.0102   1.0000
  12.500   1.0741   0.06205   0.05754  -0.0013   0.0102   1.0000
  12.750   1.0585   0.06744   0.06315  -0.0036   0.0101   1.0000
  13.000   1.0413   0.07362   0.06954  -0.0068   0.0102   1.0000
  13.250   1.0232   0.08055   0.07667  -0.0110   0.0101   1.0000
  13.500   1.0041   0.08838   0.08467  -0.0161   0.0102   1.0000
  13.750   0.9835   0.09736   0.09380  -0.0221   0.0104   1.0000
  14.000   0.9612   0.10773   0.10431  -0.0289   0.0105   1.0000
  14.250   0.9384   0.11914   0.11578  -0.0360   0.0108   1.0000
  14.500   0.9130   0.13198   0.12867  -0.0433   0.0112   1.0000
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