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S7012 8.75% (s7012-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S7012 8.75% (s7012-il)
Reynolds number: 50,000
Max Cl/Cd: 37.51 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s7012-il-50000-n5.txt
Download as CSV file: xf-s7012-il-50000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4701   0.09250   0.08561  -0.0202   1.0000   0.0440
  -8.250  -0.4722   0.08788   0.08109  -0.0229   1.0000   0.0424
  -7.750  -0.4865   0.07511   0.06844  -0.0356   1.0000   0.0385
  -7.500  -0.4839   0.07101   0.06435  -0.0371   1.0000   0.0381
  -7.250  -0.4816   0.06675   0.06005  -0.0389   1.0000   0.0376
  -7.000  -0.4785   0.06236   0.05557  -0.0407   1.0000   0.0372
  -6.750  -0.4736   0.05795   0.05097  -0.0423   1.0000   0.0367
  -6.500  -0.4662   0.05363   0.04643  -0.0435   1.0000   0.0363
  -6.250  -0.4561   0.04941   0.04191  -0.0444   1.0000   0.0360
  -6.000  -0.4430   0.04544   0.03758  -0.0449   1.0000   0.0358
  -5.750  -0.4273   0.04174   0.03343  -0.0451   1.0000   0.0363
  -5.500  -0.4089   0.03839   0.02955  -0.0450   1.0000   0.0373
  -5.250  -0.3882   0.03552   0.02608  -0.0446   1.0000   0.0385
  -5.000  -0.3677   0.03275   0.02301  -0.0442   1.0000   0.0399
  -4.750  -0.3462   0.03049   0.02050  -0.0435   1.0000   0.0413
  -4.500  -0.3237   0.02848   0.01822  -0.0425   1.0000   0.0427
  -4.250  -0.3010   0.02671   0.01617  -0.0414   1.0000   0.0448
  -4.000  -0.2786   0.02517   0.01439  -0.0400   1.0000   0.0476
  -3.750  -0.2569   0.02382   0.01290  -0.0387   1.0000   0.0530
  -3.500  -0.2350   0.02271   0.01165  -0.0376   1.0000   0.0631
  -3.250  -0.2132   0.02143   0.01045  -0.0369   1.0000   0.0823
  -3.000  -0.1902   0.01971   0.00924  -0.0367   1.0000   0.1548
  -2.750  -0.1700   0.01759   0.00854  -0.0366   1.0000   0.4080
  -2.500  -0.1599   0.01682   0.00874  -0.0322   1.0000   0.6243
  -2.250  -0.1500   0.01665   0.00874  -0.0275   1.0000   0.7424
  -2.000  -0.1400   0.01650   0.00864  -0.0229   1.0000   0.8241
  -1.750  -0.1158   0.01632   0.00836  -0.0213   1.0000   0.9148
  -1.500  -0.0634   0.01622   0.00784  -0.0268   0.9928   1.0000
  -1.250  -0.0178   0.01637   0.00760  -0.0313   0.9773   1.0000
  -1.000   0.0268   0.01652   0.00741  -0.0354   0.9619   1.0000
  -0.750   0.0707   0.01665   0.00724  -0.0391   0.9466   1.0000
  -0.500   0.1144   0.01676   0.00712  -0.0427   0.9314   1.0000
   0.000   0.1988   0.01692   0.00692  -0.0487   0.9005   1.0000
   0.250   0.2355   0.01700   0.00686  -0.0505   0.8825   1.0000
   0.500   0.2714   0.01708   0.00683  -0.0520   0.8644   1.0000
   0.750   0.3066   0.01716   0.00681  -0.0532   0.8466   1.0000
   1.000   0.3408   0.01723   0.00679  -0.0541   0.8291   1.0000
   1.250   0.3705   0.01737   0.00687  -0.0543   0.8092   1.0000
   1.500   0.4006   0.01751   0.00695  -0.0544   0.7905   1.0000
   1.750   0.4304   0.01765   0.00703  -0.0544   0.7726   1.0000
   2.000   0.4577   0.01786   0.00720  -0.0540   0.7532   1.0000
   2.250   0.4850   0.01807   0.00738  -0.0536   0.7345   1.0000
   2.500   0.5125   0.01829   0.00759  -0.0532   0.7166   1.0000
   2.750   0.5389   0.01854   0.00783  -0.0526   0.6980   1.0000
   3.000   0.5649   0.01882   0.00812  -0.0520   0.6791   1.0000
   3.250   0.5916   0.01909   0.00840  -0.0515   0.6609   1.0000
   3.500   0.6181   0.01938   0.00875  -0.0509   0.6429   1.0000
   3.750   0.6437   0.01972   0.00915  -0.0504   0.6234   1.0000
   4.000   0.6697   0.02004   0.00953  -0.0497   0.6045   1.0000
   4.250   0.6955   0.02037   0.00991  -0.0490   0.5855   1.0000
   4.500   0.7205   0.02074   0.01043  -0.0483   0.5646   1.0000
   4.750   0.7459   0.02108   0.01084  -0.0475   0.5447   1.0000
   5.000   0.7703   0.02149   0.01138  -0.0467   0.5225   1.0000
   5.250   0.7949   0.02186   0.01182  -0.0458   0.5008   1.0000
   5.500   0.8186   0.02229   0.01244  -0.0449   0.4764   1.0000
   5.750   0.8418   0.02273   0.01301  -0.0438   0.4507   1.0000
   6.000   0.8646   0.02318   0.01359  -0.0427   0.4235   1.0000
   6.250   0.8866   0.02367   0.01421  -0.0416   0.3942   1.0000
   6.500   0.9078   0.02420   0.01482  -0.0403   0.3622   1.0000
   6.750   0.9277   0.02484   0.01558  -0.0390   0.3262   1.0000
   7.000   0.9462   0.02562   0.01637  -0.0376   0.2877   1.0000
   7.250   0.9631   0.02664   0.01735  -0.0362   0.2463   1.0000
   7.500   0.9779   0.02794   0.01857  -0.0348   0.2014   1.0000
   7.750   0.9903   0.02961   0.02007  -0.0334   0.1569   1.0000
   8.000   1.0006   0.03170   0.02198  -0.0319   0.1175   1.0000
   8.250   1.0087   0.03411   0.02421  -0.0303   0.0888   1.0000
   8.500   1.0170   0.03649   0.02660  -0.0287   0.0679   1.0000
   8.750   1.0252   0.03881   0.02896  -0.0272   0.0550   1.0000
   9.000   1.0334   0.04121   0.03144  -0.0256   0.0474   1.0000
   9.250   1.0432   0.04357   0.03399  -0.0241   0.0423   1.0000
   9.500   1.0522   0.04627   0.03667  -0.0227   0.0394   1.0000
   9.750   1.0661   0.04906   0.03991  -0.0212   0.0369   1.0000
  10.000   1.0743   0.05194   0.04314  -0.0198   0.0347   1.0000
  10.250   1.0771   0.05480   0.04625  -0.0186   0.0327   1.0000
  10.500   1.0774   0.05779   0.04945  -0.0176   0.0314   1.0000
  10.750   1.0758   0.06109   0.05288  -0.0170   0.0302   1.0000
  11.000   1.0713   0.06507   0.05702  -0.0168   0.0295   1.0000
  11.250   1.0618   0.06945   0.06173  -0.0173   0.0293   1.0000
  11.500   1.0497   0.07439   0.06696  -0.0188   0.0292   1.0000
  11.750   1.0362   0.07986   0.07267  -0.0212   0.0292   1.0000
  12.000   1.0213   0.08594   0.07896  -0.0244   0.0293   1.0000
  12.250   1.0054   0.09270   0.08590  -0.0285   0.0294   1.0000
  12.500   0.9898   0.09994   0.09328  -0.0329   0.0295   1.0000
  12.750   0.9434   0.11696   0.11071  -0.0451   0.0327   1.0000
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