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S7012 8.75% (s7012-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: S7012 8.75% (s7012-il)
Reynolds number: 1,000,000
Max Cl/Cd: 96.97 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s7012-il-1000000-n5.txt
Download as CSV file: xf-s7012-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.4242   0.14555   0.14396   0.0038   1.0000   0.0058
 -13.250  -0.4209   0.14231   0.14073   0.0022   1.0000   0.0059
 -12.750  -0.5270   0.14542   0.14366   0.0059   1.0000   0.0058
  -7.750  -0.5871   0.03135   0.02898  -0.0471   1.0000   0.0035
  -7.500  -0.5658   0.02627   0.02343  -0.0498   0.9968   0.0035
  -7.250  -0.5409   0.02202   0.01865  -0.0519   0.9918   0.0035
  -7.000  -0.5150   0.01809   0.01417  -0.0534   0.9855   0.0036
  -6.750  -0.4871   0.01556   0.01127  -0.0545   0.9797   0.0038
  -6.500  -0.4554   0.01432   0.00985  -0.0559   0.9742   0.0039
  -6.250  -0.4226   0.01340   0.00881  -0.0573   0.9679   0.0041
  -6.000  -0.3894   0.01261   0.00790  -0.0587   0.9595   0.0042
  -5.750  -0.3573   0.01191   0.00708  -0.0598   0.9477   0.0045
  -5.500  -0.3270   0.01127   0.00632  -0.0604   0.9314   0.0047
  -5.250  -0.2994   0.01073   0.00565  -0.0604   0.9112   0.0050
  -5.000  -0.2732   0.01027   0.00504  -0.0600   0.8891   0.0051
  -4.750  -0.2472   0.00987   0.00450  -0.0596   0.8667   0.0053
  -4.500  -0.2213   0.00952   0.00400  -0.0591   0.8438   0.0054
  -4.250  -0.1950   0.00921   0.00355  -0.0588   0.8212   0.0056
  -4.000  -0.1684   0.00904   0.00328  -0.0584   0.7991   0.0058
  -3.750  -0.1417   0.00886   0.00299  -0.0582   0.7770   0.0060
  -3.500  -0.1149   0.00853   0.00251  -0.0579   0.7558   0.0062
  -3.250  -0.0879   0.00829   0.00214  -0.0577   0.7341   0.0063
  -3.000  -0.0607   0.00813   0.00185  -0.0575   0.7129   0.0066
  -2.750  -0.0333   0.00800   0.00161  -0.0573   0.6923   0.0071
  -2.500  -0.0058   0.00791   0.00143  -0.0572   0.6736   0.0082
  -2.250   0.0219   0.00783   0.00127  -0.0571   0.6559   0.0108
  -2.000   0.0494   0.00761   0.00112  -0.0571   0.6390   0.0427
  -1.750   0.0768   0.00734   0.00100  -0.0571   0.6221   0.1038
  -1.500   0.1041   0.00698   0.00089  -0.0573   0.6059   0.2004
  -1.250   0.1316   0.00670   0.00082  -0.0574   0.5893   0.2864
  -1.000   0.1589   0.00637   0.00077  -0.0576   0.5735   0.3973
  -0.750   0.1865   0.00618   0.00074  -0.0577   0.5577   0.4719
  -0.500   0.2142   0.00604   0.00073  -0.0577   0.5423   0.5381
  -0.250   0.2418   0.00594   0.00074  -0.0577   0.5278   0.6002
   0.000   0.2696   0.00592   0.00077  -0.0577   0.5144   0.6388
   0.500   0.3254   0.00597   0.00082  -0.0576   0.4893   0.6838
   0.750   0.3533   0.00602   0.00085  -0.0576   0.4760   0.7014
   1.000   0.3811   0.00607   0.00090  -0.0575   0.4620   0.7171
   1.500   0.4367   0.00619   0.00100  -0.0574   0.4371   0.7454
   1.750   0.4644   0.00625   0.00106  -0.0573   0.4248   0.7604
   2.000   0.4920   0.00631   0.00112  -0.0573   0.4118   0.7753
   2.250   0.5195   0.00639   0.00120  -0.0572   0.3965   0.7892
   2.500   0.5467   0.00649   0.00129  -0.0570   0.3781   0.8056
   2.750   0.5736   0.00660   0.00138  -0.0568   0.3592   0.8240
   3.000   0.6004   0.00669   0.00149  -0.0566   0.3439   0.8445
   3.250   0.6264   0.00677   0.00161  -0.0561   0.3276   0.8699
   3.500   0.6510   0.00688   0.00173  -0.0554   0.3067   0.9005
   3.750   0.6735   0.00700   0.00186  -0.0541   0.2809   0.9395
   4.000   0.7030   0.00725   0.00200  -0.0546   0.2483   1.0000
   4.250   0.7291   0.00765   0.00223  -0.0545   0.2088   1.0000
   4.500   0.7548   0.00811   0.00248  -0.0543   0.1669   1.0000
   4.750   0.7800   0.00864   0.00278  -0.0540   0.1210   1.0000
   5.000   0.8054   0.00913   0.00310  -0.0538   0.0859   1.0000
   5.250   0.8312   0.00956   0.00341  -0.0536   0.0610   1.0000
   5.500   0.8568   0.01001   0.00375  -0.0534   0.0396   1.0000
   5.750   0.8814   0.01061   0.00420  -0.0530   0.0144   1.0000
   6.000   0.9070   0.01106   0.00461  -0.0527   0.0059   1.0000
   6.250   0.9331   0.01140   0.00497  -0.0525   0.0048   1.0000
   6.500   0.9592   0.01175   0.00536  -0.0522   0.0043   1.0000
   6.750   0.9850   0.01212   0.00577  -0.0520   0.0041   1.0000
   7.000   1.0107   0.01248   0.00618  -0.0517   0.0039   1.0000
   7.250   1.0360   0.01289   0.00663  -0.0514   0.0038   1.0000
   7.500   1.0610   0.01333   0.00714  -0.0510   0.0036   1.0000
   7.750   1.0857   0.01382   0.00769  -0.0506   0.0034   1.0000
   8.000   1.1099   0.01435   0.00828  -0.0501   0.0033   1.0000
   8.250   1.1336   0.01492   0.00892  -0.0496   0.0031   1.0000
   8.500   1.1568   0.01555   0.00961  -0.0491   0.0030   1.0000
   8.750   1.1794   0.01623   0.01036  -0.0484   0.0029   1.0000
   9.000   1.2013   0.01698   0.01121  -0.0477   0.0028   1.0000
   9.250   1.2224   0.01779   0.01210  -0.0469   0.0027   1.0000
   9.500   1.2423   0.01871   0.01312  -0.0459   0.0026   1.0000
   9.750   1.2613   0.01969   0.01420  -0.0449   0.0026   1.0000
  10.000   1.2788   0.02078   0.01540  -0.0437   0.0025   1.0000
  10.250   1.2941   0.02206   0.01681  -0.0422   0.0025   1.0000
  10.500   1.3063   0.02359   0.01848  -0.0404   0.0024   1.0000
  10.750   1.3113   0.02582   0.02091  -0.0379   0.0023   1.0000
  11.000   1.3249   0.02691   0.02211  -0.0364   0.0023   1.0000
  11.250   1.3332   0.02829   0.02364  -0.0342   0.0023   1.0000
  11.500   1.3362   0.02969   0.02516  -0.0313   0.0023   1.0000
  11.750   1.3379   0.03116   0.02676  -0.0286   0.0022   1.0000
  12.000   1.3374   0.03295   0.02868  -0.0263   0.0022   1.0000
  12.250   1.3355   0.03505   0.03092  -0.0245   0.0022   1.0000
  12.500   1.3333   0.03741   0.03342  -0.0233   0.0022   1.0000
  12.750   1.3281   0.04036   0.03653  -0.0227   0.0022   1.0000
  13.000   1.3241   0.04349   0.03980  -0.0228   0.0022   1.0000
  13.250   1.3159   0.04748   0.04395  -0.0236   0.0022   1.0000
  13.500   1.3077   0.05183   0.04845  -0.0250   0.0022   1.0000
  13.750   1.3007   0.05632   0.05309  -0.0270   0.0022   1.0000
  14.000   1.2915   0.06144   0.05834  -0.0294   0.0022   1.0000
  14.250   1.2743   0.06821   0.06528  -0.0329   0.0022   1.0000
  14.500   1.2632   0.07427   0.07148  -0.0362   0.0022   1.0000
  14.750   1.2472   0.08152   0.07887  -0.0403   0.0022   1.0000
  15.000   1.2281   0.08977   0.08727  -0.0451   0.0022   1.0000
  15.250   1.2131   0.09771   0.09534  -0.0498   0.0022   1.0000
  15.500   1.1930   0.10712   0.10489  -0.0553   0.0022   1.0000
  15.750   1.1746   0.11659   0.11449  -0.0609   0.0022   1.0000
  16.000   1.1565   0.12636   0.12438  -0.0666   0.0022   1.0000
  16.250   1.1359   0.13716   0.13530  -0.0729   0.0022   1.0000
  16.500   1.1165   0.14811   0.14636  -0.0793   0.0022   1.0000
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