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

S7012 8.75% (s7012-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: S7012 8.75% (s7012-il)
Reynolds number: 500,000
Max Cl/Cd: 85.68 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s7012-il-500000-n5.txt
Download as CSV file: xf-s7012-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.4490   0.04735   0.04541  -0.0350   1.0000   0.0072
  -7.250  -0.5216   0.03996   0.03730  -0.0456   1.0000   0.0059
  -7.000  -0.5193   0.03399   0.03095  -0.0459   1.0000   0.0057
  -6.750  -0.5116   0.02872   0.02522  -0.0454   1.0000   0.0057
  -6.500  -0.4836   0.02386   0.01976  -0.0479   0.9960   0.0057
  -6.250  -0.4536   0.02068   0.01607  -0.0496   0.9912   0.0057
  -6.000  -0.4219   0.01860   0.01361  -0.0510   0.9859   0.0059
  -5.750  -0.3913   0.01667   0.01132  -0.0521   0.9800   0.0061
  -5.500  -0.3601   0.01475   0.00913  -0.0532   0.9743   0.0064
  -5.250  -0.3275   0.01366   0.00790  -0.0545   0.9684   0.0067
  -5.000  -0.2949   0.01280   0.00694  -0.0557   0.9608   0.0069
  -4.750  -0.2617   0.01212   0.00618  -0.0570   0.9522   0.0074
  -4.500  -0.2281   0.01154   0.00552  -0.0583   0.9417   0.0081
  -4.250  -0.1959   0.01092   0.00480  -0.0592   0.9277   0.0084
  -4.000  -0.1656   0.01036   0.00413  -0.0597   0.9106   0.0085
  -3.750  -0.1369   0.00993   0.00358  -0.0598   0.8908   0.0087
  -3.500  -0.1093   0.00960   0.00312  -0.0595   0.8696   0.0090
  -3.250  -0.0823   0.00936   0.00272  -0.0592   0.8475   0.0093
  -3.000  -0.0555   0.00913   0.00235  -0.0588   0.8251   0.0102
  -2.750  -0.0287   0.00897   0.00207  -0.0584   0.8027   0.0125
  -2.500  -0.0021   0.00869   0.00181  -0.0581   0.7803   0.0387
  -2.250   0.0241   0.00828   0.00159  -0.0580   0.7585   0.1153
  -2.000   0.0505   0.00787   0.00144  -0.0579   0.7371   0.2092
  -1.750   0.0770   0.00753   0.00133  -0.0579   0.7166   0.3047
  -1.500   0.1032   0.00704   0.00123  -0.0579   0.6973   0.4486
  -1.250   0.1297   0.00676   0.00118  -0.0578   0.6785   0.5449
  -1.000   0.1563   0.00664   0.00119  -0.0575   0.6602   0.6185
  -0.750   0.1834   0.00664   0.00119  -0.0572   0.6428   0.6581
  -0.500   0.2106   0.00666   0.00119  -0.0570   0.6252   0.6856
  -0.250   0.2377   0.00669   0.00119  -0.0567   0.6079   0.7077
   0.000   0.2649   0.00674   0.00120  -0.0565   0.5909   0.7275
   0.500   0.3192   0.00685   0.00124  -0.0560   0.5587   0.7625
   0.750   0.3463   0.00690   0.00128  -0.0557   0.5441   0.7784
   1.000   0.3733   0.00695   0.00132  -0.0554   0.5299   0.7948
   1.750   0.4529   0.00713   0.00149  -0.0543   0.4873   0.8479
   2.250   0.5031   0.00720   0.00164  -0.0528   0.4607   0.8951
   2.750   0.5594   0.00728   0.00174  -0.0526   0.4321   0.9838
   3.000   0.5880   0.00743   0.00183  -0.0529   0.4156   1.0000
   3.250   0.6156   0.00760   0.00195  -0.0529   0.3977   1.0000
   3.500   0.6430   0.00777   0.00208  -0.0529   0.3797   1.0000
   3.750   0.6703   0.00796   0.00222  -0.0528   0.3622   1.0000
   4.000   0.6974   0.00819   0.00237  -0.0528   0.3408   1.0000
   4.250   0.7240   0.00847   0.00257  -0.0527   0.3140   1.0000
   4.500   0.7506   0.00876   0.00278  -0.0525   0.2896   1.0000
   4.750   0.7767   0.00911   0.00302  -0.0524   0.2583   1.0000
   5.000   0.8017   0.00962   0.00332  -0.0521   0.2130   1.0000
   5.250   0.8253   0.01036   0.00374  -0.0517   0.1522   1.0000
   5.500   0.8497   0.01097   0.00414  -0.0514   0.1105   1.0000
   5.750   0.8746   0.01149   0.00454  -0.0511   0.0825   1.0000
   6.000   0.8992   0.01205   0.00498  -0.0508   0.0569   1.0000
   6.250   0.9231   0.01272   0.00552  -0.0504   0.0312   1.0000
   6.500   0.9468   0.01341   0.00612  -0.0499   0.0132   1.0000
   6.750   0.9711   0.01399   0.00669  -0.0494   0.0080   1.0000
   7.000   0.9956   0.01453   0.00727  -0.0490   0.0065   1.0000
   7.250   1.0202   0.01503   0.00785  -0.0486   0.0061   1.0000
   7.500   1.0444   0.01559   0.00849  -0.0481   0.0056   1.0000
   7.750   1.0681   0.01618   0.00920  -0.0476   0.0054   1.0000
   8.000   1.0912   0.01686   0.00996  -0.0470   0.0051   1.0000
   8.250   1.1133   0.01762   0.01082  -0.0463   0.0048   1.0000
   8.500   1.1344   0.01851   0.01180  -0.0455   0.0046   1.0000
   8.750   1.1535   0.01960   0.01301  -0.0444   0.0044   1.0000
   9.000   1.1701   0.02094   0.01449  -0.0431   0.0042   1.0000
   9.250   1.1865   0.02225   0.01594  -0.0417   0.0041   1.0000
   9.500   1.2035   0.02340   0.01722  -0.0405   0.0041   1.0000
   9.750   1.2191   0.02466   0.01861  -0.0391   0.0040   1.0000
  10.000   1.2334   0.02601   0.02010  -0.0376   0.0040   1.0000
  10.250   1.2458   0.02749   0.02173  -0.0359   0.0039   1.0000
  10.500   1.2565   0.02903   0.02343  -0.0341   0.0039   1.0000
  10.750   1.2635   0.03069   0.02524  -0.0319   0.0039   1.0000
  11.000   1.2664   0.03241   0.02713  -0.0292   0.0039   1.0000
  11.250   1.2673   0.03429   0.02919  -0.0267   0.0039   1.0000
  11.500   1.2666   0.03641   0.03148  -0.0246   0.0038   1.0000
  11.750   1.2654   0.03867   0.03392  -0.0231   0.0038   1.0000
  12.000   1.2625   0.04132   0.03675  -0.0221   0.0038   1.0000
  12.250   1.2579   0.04438   0.04003  -0.0217   0.0037   1.0000
  12.500   1.2530   0.04775   0.04358  -0.0219   0.0037   1.0000
  12.750   1.2450   0.05184   0.04785  -0.0228   0.0037   1.0000
  13.000   1.2375   0.05616   0.05235  -0.0244   0.0036   1.0000
  13.250   1.2263   0.06137   0.05775  -0.0266   0.0036   1.0000
  13.500   1.2147   0.06701   0.06356  -0.0295   0.0036   1.0000
  13.750   1.2032   0.07292   0.06965  -0.0328   0.0035   1.0000
  14.000   1.1900   0.07951   0.07639  -0.0365   0.0035   1.0000
  14.250   1.1707   0.08760   0.08466  -0.0413   0.0036   1.0000
  14.500   1.1561   0.09528   0.09249  -0.0459   0.0035   1.0000
  14.750   1.1382   0.10414   0.10150  -0.0513   0.0036   1.0000
  15.000   1.1188   0.11388   0.11139  -0.0572   0.0036   1.0000
  15.250   1.1009   0.12382   0.12147  -0.0632   0.0036   1.0000
  15.500   1.0800   0.13508   0.13282  -0.0699   0.0037   1.0000
  15.750   1.0589   0.14700   0.14486  -0.0768   0.0038   1.0000
  16.000   1.0333   0.16118   0.15914  -0.0847   0.0039   1.0000
<< Back to S7012 8.75% (s7012-il)

Polar data table (+)

Polar graphs


<< Back to S7012 8.75% (s7012-il)