Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

S1012 (s1012-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S1012 (s1012-il)
Reynolds number: 100,000
Max Cl/Cd: 37.24 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s1012-il-100000.txt
Download as CSV file: xf-s1012-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S1012                                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.5135   0.11541   0.11043  -0.0203   1.0000   0.1712
 -11.500  -0.8515   0.06949   0.06368  -0.0439   1.0000   0.0846
 -11.250  -0.8677   0.06507   0.05914  -0.0423   1.0000   0.0843
 -11.000  -0.8873   0.06121   0.05510  -0.0394   1.0000   0.0841
 -10.750  -0.9034   0.05732   0.05094  -0.0366   1.0000   0.0841
 -10.500  -0.9195   0.05391   0.04715  -0.0330   1.0000   0.0845
 -10.250  -0.9169   0.05008   0.04325  -0.0315   1.0000   0.0864
 -10.000  -0.8938   0.04917   0.04251  -0.0313   1.0000   0.0903
  -9.750  -0.8971   0.04648   0.03956  -0.0282   1.0000   0.0921
  -9.500  -0.9027   0.04385   0.03660  -0.0242   1.0000   0.0935
  -9.250  -0.9106   0.04173   0.03413  -0.0193   1.0000   0.0952
  -9.000  -0.9192   0.04010   0.03207  -0.0139   1.0000   0.0971
  -8.750  -0.9178   0.03792   0.02973  -0.0103   1.0000   0.0997
  -8.500  -0.9074   0.03669   0.02852  -0.0079   1.0000   0.1030
  -8.250  -0.9000   0.03531   0.02693  -0.0049   1.0000   0.1064
  -8.000  -0.8945   0.03391   0.02512  -0.0013   1.0000   0.1104
  -7.750  -0.8822   0.03213   0.02321   0.0008   1.0000   0.1144
  -7.500  -0.8675   0.03102   0.02205   0.0028   1.0000   0.1190
  -7.250  -0.8546   0.02996   0.02068   0.0052   1.0000   0.1246
  -7.000  -0.8373   0.02855   0.01923   0.0067   1.0000   0.1299
  -6.750  -0.8203   0.02760   0.01817   0.0084   1.0000   0.1360
  -6.500  -0.8027   0.02650   0.01691   0.0101   1.0000   0.1430
  -6.250  -0.7841   0.02564   0.01608   0.0114   1.0000   0.1504
  -6.000  -0.7647   0.02468   0.01502   0.0128   1.0000   0.1585
  -5.750  -0.7458   0.02396   0.01429   0.0142   1.0000   0.1681
  -5.500  -0.7261   0.02309   0.01348   0.0154   1.0000   0.1781
  -5.250  -0.7069   0.02234   0.01272   0.0168   1.0000   0.1899
  -5.000  -0.6881   0.02165   0.01207   0.0183   1.0000   0.2039
  -4.750  -0.6696   0.02093   0.01145   0.0197   1.0000   0.2200
  -4.500  -0.6519   0.02020   0.01090   0.0213   1.0000   0.2397
  -4.250  -0.6346   0.01949   0.01036   0.0229   1.0000   0.2662
  -4.000  -0.6190   0.01865   0.00986   0.0248   1.0000   0.3027
  -3.750  -0.6060   0.01761   0.00938   0.0272   1.0000   0.3704
  -3.500  -0.6016   0.01615   0.00921   0.0317   1.0000   0.5471
  -3.250  -0.5933   0.01691   0.01077   0.0384   1.0000   0.7416
  -3.000  -0.5822   0.01758   0.01137   0.0431   1.0000   0.7939
  -2.750  -0.5687   0.01830   0.01202   0.0475   1.0000   0.8274
  -2.500  -0.5511   0.01902   0.01267   0.0512   1.0000   0.8544
  -2.250  -0.5331   0.01960   0.01315   0.0545   1.0000   0.8794
  -2.000  -0.4836   0.02079   0.01421   0.0523   1.0000   0.9005
  -1.750  -0.4051   0.02217   0.01540   0.0441   1.0000   0.9191
  -1.500  -0.3173   0.02321   0.01627   0.0336   1.0000   0.9355
  -1.250  -0.2440   0.02379   0.01673   0.0251   1.0000   0.9521
  -1.000  -0.1674   0.02419   0.01704   0.0157   1.0000   0.9706
  -0.750  -0.0632   0.02424   0.01701   0.0006   1.0000   0.9916
  -0.500  -0.0142   0.02414   0.01688  -0.0048   1.0000   1.0000
  -0.250  -0.0071   0.02411   0.01683  -0.0024   1.0000   1.0000
   0.000   0.0000   0.02409   0.01682   0.0000   1.0000   1.0000
   0.250   0.0072   0.02410   0.01683   0.0024   1.0000   1.0000
   0.500   0.0142   0.02414   0.01688   0.0048   1.0000   1.0000
   0.750   0.0650   0.02423   0.01700  -0.0009   0.9911   1.0000
   1.000   0.1680   0.02419   0.01704  -0.0158   0.9705   1.0000
   1.250   0.2452   0.02376   0.01670  -0.0253   0.9516   1.0000
   1.500   0.3172   0.02321   0.01627  -0.0335   0.9356   1.0000
   1.750   0.4040   0.02219   0.01542  -0.0440   0.9193   1.0000
   2.000   0.4843   0.02076   0.01418  -0.0524   0.9003   1.0000
   2.250   0.5329   0.01959   0.01314  -0.0544   0.8793   1.0000
   2.500   0.5510   0.01904   0.01268  -0.0512   0.8547   1.0000
   2.750   0.5687   0.01829   0.01201  -0.0475   0.8274   1.0000
   3.000   0.5822   0.01759   0.01138  -0.0431   0.7942   1.0000
   3.250   0.5933   0.01692   0.01077  -0.0385   0.7420   1.0000
   3.500   0.6015   0.01615   0.00920  -0.0317   0.5472   1.0000
   3.750   0.6060   0.01760   0.00937  -0.0272   0.3712   1.0000
   4.000   0.6189   0.01864   0.00986  -0.0248   0.3029   1.0000
   4.250   0.6346   0.01948   0.01035  -0.0229   0.2663   1.0000
   4.500   0.6519   0.02020   0.01090  -0.0212   0.2396   1.0000
   4.750   0.6695   0.02092   0.01144  -0.0197   0.2200   1.0000
   5.000   0.6881   0.02166   0.01207  -0.0182   0.2039   1.0000
   5.250   0.7068   0.02234   0.01272  -0.0168   0.1898   1.0000
   5.500   0.7260   0.02309   0.01348  -0.0154   0.1779   1.0000
   5.750   0.7458   0.02396   0.01428  -0.0142   0.1682   1.0000
   6.000   0.7647   0.02468   0.01502  -0.0128   0.1585   1.0000
   6.250   0.7840   0.02564   0.01608  -0.0114   0.1504   1.0000
   6.500   0.8027   0.02650   0.01691  -0.0100   0.1430   1.0000
   6.750   0.8203   0.02760   0.01818  -0.0084   0.1361   1.0000
   7.000   0.8373   0.02854   0.01921  -0.0067   0.1299   1.0000
   7.250   0.8545   0.02996   0.02069  -0.0052   0.1245   1.0000
   7.500   0.8675   0.03102   0.02205  -0.0028   0.1190   1.0000
   7.750   0.8822   0.03214   0.02322  -0.0008   0.1145   1.0000
   8.000   0.8944   0.03391   0.02512   0.0013   0.1103   1.0000
   8.250   0.8999   0.03529   0.02691   0.0049   0.1065   1.0000
   8.500   0.9074   0.03668   0.02851   0.0079   0.1029   1.0000
   8.750   0.9178   0.03790   0.02971   0.0103   0.0996   1.0000
   9.000   0.9190   0.04006   0.03204   0.0139   0.0970   1.0000
   9.250   0.9104   0.04172   0.03412   0.0193   0.0951   1.0000
   9.500   0.9027   0.04384   0.03658   0.0242   0.0935   1.0000
   9.750   0.8972   0.04646   0.03953   0.0282   0.0920   1.0000
  10.000   0.8934   0.04925   0.04260   0.0313   0.0904   1.0000
  10.250   0.9164   0.05012   0.04331   0.0316   0.0865   1.0000
  10.500   0.9190   0.05383   0.04708   0.0331   0.0845   1.0000
  10.750   0.9036   0.05735   0.05097   0.0365   0.0841   1.0000
  11.000   0.8874   0.06124   0.05513   0.0394   0.0842   1.0000
  11.250   0.8696   0.06514   0.05920   0.0421   0.0844   1.0000
  11.500   0.8522   0.06956   0.06374   0.0438   0.0846   1.0000
  11.750   0.7072   0.08611   0.08079   0.0377   0.0965   1.0000
  12.000   0.7012   0.09220   0.08689   0.0356   0.0973   1.0000
<< Back to S1012 (s1012-il)

Polar data table (+)

Polar graphs


<< Back to S1012 (s1012-il)