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S7012 8.75% (s7012-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S7012 8.75% (s7012-il)
Reynolds number: 50,000
Max Cl/Cd: 33.73 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s7012-il-50000.txt
Download as CSV file: xf-s7012-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S7012 8.75%                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4725   0.11853   0.11158  -0.0024   1.0000   0.2047
  -9.250  -0.4664   0.11463   0.10773  -0.0028   1.0000   0.2112
  -9.000  -0.4725   0.11291   0.10610  -0.0044   1.0000   0.2204
  -8.750  -0.4557   0.10798   0.10117  -0.0035   1.0000   0.2296
  -8.500  -0.4583   0.10522   0.09850  -0.0046   1.0000   0.2379
  -8.250  -0.4654   0.10345   0.09683  -0.0057   1.0000   0.2491
  -8.000  -0.4483   0.09883   0.09222  -0.0046   1.0000   0.2609
  -7.750  -0.4402   0.09522   0.08866  -0.0043   1.0000   0.2714
  -7.500  -0.4365   0.09208   0.08560  -0.0040   1.0000   0.2852
  -7.250  -0.4327   0.08910   0.08265  -0.0036   1.0000   0.2995
  -7.000  -0.4365   0.08683   0.08049  -0.0028   1.0000   0.3183
  -6.750  -0.4462   0.08497   0.07878  -0.0020   1.0000   0.3342
  -6.500  -0.4203   0.08038   0.07417   0.0000   1.0000   0.3559
  -6.250  -0.4391   0.07930   0.07326   0.0011   1.0000   0.3772
  -5.500  -0.4227   0.04905   0.04177  -0.0436   1.0000   0.1216
  -5.250  -0.4034   0.04374   0.03577  -0.0452   1.0000   0.1102
  -5.000  -0.3828   0.04014   0.03179  -0.0451   1.0000   0.1081
  -4.750  -0.3612   0.03670   0.02794  -0.0450   1.0000   0.1070
  -4.500  -0.3378   0.03349   0.02428  -0.0447   1.0000   0.1057
  -4.250  -0.3131   0.03062   0.02096  -0.0441   1.0000   0.1052
  -4.000  -0.2876   0.02817   0.01804  -0.0432   1.0000   0.1070
  -3.750  -0.2633   0.02602   0.01569  -0.0422   1.0000   0.1137
  -3.500  -0.2398   0.02428   0.01389  -0.0410   1.0000   0.1291
  -3.250  -0.2165   0.02253   0.01218  -0.0394   1.0000   0.1544
  -3.000  -0.1939   0.02029   0.01049  -0.0382   1.0000   0.2407
  -2.750  -0.1923   0.01699   0.01005  -0.0308   1.0000   0.6669
  -2.500  -0.2007   0.01683   0.01024  -0.0199   1.0000   0.8286
  -2.250  -0.0963   0.01651   0.00896  -0.0299   1.0000   1.0000
  -2.000  -0.1026   0.01624   0.00854  -0.0263   1.0000   1.0000
  -1.750  -0.0941   0.01615   0.00814  -0.0247   1.0000   1.0000
  -1.500  -0.0777   0.01619   0.00788  -0.0243   1.0000   1.0000
  -1.250  -0.0589   0.01634   0.00773  -0.0242   1.0000   1.0000
  -1.000  -0.0395   0.01657   0.00770  -0.0242   1.0000   1.0000
  -0.750  -0.0201   0.01688   0.00777  -0.0242   1.0000   1.0000
  -0.500  -0.0011   0.01726   0.00791  -0.0243   1.0000   1.0000
  -0.250   0.0176   0.01772   0.00818  -0.0244   1.0000   1.0000
   0.000   0.0359   0.01825   0.00855  -0.0246   1.0000   1.0000
   0.250   0.0538   0.01885   0.00902  -0.0249   1.0000   1.0000
   0.500   0.0722   0.01953   0.00958  -0.0253   0.9996   1.0000
   0.750   0.1316   0.02066   0.01054  -0.0331   0.9795   1.0000
   1.000   0.1881   0.02161   0.01139  -0.0399   0.9596   1.0000
   1.250   0.2419   0.02241   0.01213  -0.0459   0.9397   1.0000
   1.500   0.2907   0.02306   0.01277  -0.0506   0.9194   1.0000
   1.750   0.3453   0.02360   0.01333  -0.0560   0.9008   1.0000
   2.000   0.3874   0.02409   0.01387  -0.0591   0.8804   1.0000
   2.250   0.4367   0.02443   0.01428  -0.0629   0.8614   1.0000
   2.500   0.4867   0.02459   0.01455  -0.0663   0.8437   1.0000
   2.750   0.5185   0.02503   0.01510  -0.0669   0.8227   1.0000
   3.000   0.5587   0.02519   0.01536  -0.0682   0.8038   1.0000
   3.250   0.5929   0.02544   0.01572  -0.0684   0.7842   1.0000
   3.500   0.6233   0.02575   0.01614  -0.0681   0.7635   1.0000
   3.750   0.6586   0.02575   0.01631  -0.0677   0.7446   1.0000
   4.000   0.6823   0.02628   0.01695  -0.0664   0.7218   1.0000
   4.250   0.7133   0.02632   0.01710  -0.0651   0.7014   1.0000
   4.500   0.7375   0.02675   0.01767  -0.0636   0.6778   1.0000
   4.750   0.7629   0.02707   0.01816  -0.0619   0.6544   1.0000
   5.000   0.7916   0.02707   0.01824  -0.0599   0.6314   1.0000
   5.250   0.8152   0.02744   0.01875  -0.0580   0.6049   1.0000
   5.500   0.8395   0.02771   0.01913  -0.0559   0.5773   1.0000
   5.750   0.8642   0.02789   0.01945  -0.0537   0.5484   1.0000
   6.000   0.8885   0.02808   0.01971  -0.0515   0.5172   1.0000
   6.250   0.9104   0.02842   0.02016  -0.0492   0.4822   1.0000
   6.500   0.9336   0.02850   0.02024  -0.0467   0.4446   1.0000
   6.750   0.9551   0.02864   0.02035  -0.0441   0.4023   1.0000
   7.000   0.9744   0.02889   0.02057  -0.0414   0.3548   1.0000
   7.250   0.9910   0.02943   0.02088  -0.0386   0.3012   1.0000
   7.500   1.0041   0.03059   0.02169  -0.0357   0.2434   1.0000
   7.750   1.0155   0.03264   0.02338  -0.0331   0.1890   1.0000
   8.000   1.0288   0.03531   0.02576  -0.0310   0.1469   1.0000
   8.250   1.0445   0.03814   0.02842  -0.0294   0.1188   1.0000
   8.500   1.0626   0.04146   0.03184  -0.0280   0.1020   1.0000
   8.750   1.0821   0.04493   0.03532  -0.0271   0.0909   1.0000
   9.000   1.0936   0.04897   0.04020  -0.0253   0.0876   1.0000
   9.250   1.1016   0.05337   0.04518  -0.0237   0.0855   1.0000
   9.500   1.1046   0.05780   0.05010  -0.0221   0.0840   1.0000
   9.750   1.1027   0.06227   0.05498  -0.0208   0.0829   1.0000
  10.000   1.0947   0.06688   0.05996  -0.0196   0.0824   1.0000
  10.250   1.0745   0.07202   0.06548  -0.0187   0.0838   1.0000
  10.500   1.0499   0.07693   0.07061  -0.0182   0.0856   1.0000
  10.750   1.0251   0.08246   0.07628  -0.0195   0.0873   1.0000
  11.000   1.0041   0.08864   0.08255  -0.0222   0.0889   1.0000
  11.250   0.9872   0.09538   0.08933  -0.0255   0.0900   1.0000
  11.500   0.9783   0.10208   0.09604  -0.0283   0.0909   1.0000
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