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S9037 (9%) (s9037-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S9037 (9%) (s9037-il)
Reynolds number: 50,000
Max Cl/Cd: 34.71 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s9037-il-50000.txt
Download as CSV file: xf-s9037-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S9037 (9%)                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3640   0.10217   0.09588  -0.0258   1.0000   0.2042
  -7.500  -0.3393   0.09658   0.09025  -0.0239   1.0000   0.2155
  -7.250  -0.3714   0.09749   0.09144  -0.0235   1.0000   0.2186
  -7.000  -0.3492   0.09245   0.08637  -0.0213   1.0000   0.2306
  -6.750  -0.3515   0.08979   0.08383  -0.0195   1.0000   0.2376
  -6.500  -0.3687   0.08900   0.08321  -0.0184   1.0000   0.2464
  -6.250  -0.3614   0.08560   0.07988  -0.0156   1.0000   0.2557
  -6.000  -0.3752   0.08396   0.07838  -0.0144   1.0000   0.2647
  -5.750  -0.3912   0.08315   0.07768  -0.0142   1.0000   0.2763
  -5.500  -0.3864   0.08004   0.07465  -0.0106   1.0000   0.2892
  -5.250  -0.3863   0.07745   0.07214  -0.0078   1.0000   0.3013
  -5.000  -0.3980   0.07595   0.07072  -0.0073   1.0000   0.3194
  -4.750  -0.3987   0.07328   0.06815  -0.0045   1.0000   0.3359
  -4.500  -0.3959   0.07057   0.06551  -0.0005   1.0000   0.3538
  -3.750  -0.3030   0.04999   0.04334  -0.0412   1.0000   0.1613
  -3.500  -0.2744   0.04426   0.03721  -0.0433   1.0000   0.1287
  -3.250  -0.2433   0.03992   0.03210  -0.0457   1.0000   0.1167
  -3.000  -0.2177   0.03696   0.02873  -0.0463   1.0000   0.1151
  -2.750  -0.1899   0.03420   0.02546  -0.0469   1.0000   0.1135
  -2.500  -0.1621   0.03181   0.02251  -0.0470   1.0000   0.1132
  -2.250  -0.1358   0.02996   0.02019  -0.0469   1.0000   0.1211
  -2.000  -0.1106   0.02853   0.01839  -0.0463   1.0000   0.1318
  -1.750  -0.0871   0.02719   0.01704  -0.0458   1.0000   0.1515
  -1.500  -0.0634   0.02601   0.01585  -0.0449   1.0000   0.1865
  -1.250  -0.0357   0.02461   0.01478  -0.0448   1.0000   0.2742
  -1.000  -0.0155   0.02078   0.01366  -0.0413   1.0000   1.0000
  -0.750   0.0059   0.02128   0.01343  -0.0411   1.0000   1.0000
  -0.500   0.0259   0.02183   0.01352  -0.0408   1.0000   1.0000
  -0.250   0.0451   0.02243   0.01376  -0.0406   1.0000   1.0000
   0.000   0.0640   0.02308   0.01410  -0.0405   1.0000   1.0000
   0.250   0.0989   0.02411   0.01478  -0.0434   0.9928   1.0000
   0.500   0.1479   0.02537   0.01570  -0.0488   0.9771   1.0000
   0.750   0.1946   0.02654   0.01660  -0.0536   0.9613   1.0000
   1.000   0.2403   0.02763   0.01746  -0.0580   0.9452   1.0000
   1.250   0.2861   0.02866   0.01832  -0.0622   0.9292   1.0000
   1.500   0.3274   0.02957   0.01908  -0.0655   0.9126   1.0000
   1.750   0.3628   0.03037   0.01979  -0.0677   0.8951   1.0000
   2.000   0.4005   0.03114   0.02050  -0.0701   0.8777   1.0000
   2.250   0.4408   0.03184   0.02116  -0.0726   0.8606   1.0000
   2.500   0.4834   0.03243   0.02173  -0.0753   0.8440   1.0000
   2.750   0.5181   0.03302   0.02231  -0.0766   0.8263   1.0000
   3.000   0.5496   0.03359   0.02291  -0.0774   0.8080   1.0000
   3.250   0.5885   0.03395   0.02333  -0.0789   0.7906   1.0000
   3.500   0.6317   0.03407   0.02352  -0.0807   0.7741   1.0000
   3.750   0.6769   0.03394   0.02348  -0.0824   0.7582   1.0000
   4.000   0.7001   0.03449   0.02414  -0.0814   0.7384   1.0000
   4.250   0.7361   0.03440   0.02415  -0.0814   0.7208   1.0000
   4.500   0.7765   0.03391   0.02378  -0.0815   0.7039   1.0000
   4.750   0.8190   0.03313   0.02317  -0.0814   0.6875   1.0000
   5.000   0.8410   0.03351   0.02366  -0.0798   0.6662   1.0000
   5.250   0.8784   0.03285   0.02313  -0.0790   0.6477   1.0000
   5.500   0.9144   0.03222   0.02260  -0.0779   0.6285   1.0000
   5.750   0.9410   0.03220   0.02275  -0.0763   0.6063   1.0000
   6.000   0.9730   0.03176   0.02240  -0.0748   0.5842   1.0000
   6.250   1.0044   0.03136   0.02206  -0.0733   0.5608   1.0000
   6.500   1.0285   0.03157   0.02241  -0.0715   0.5358   1.0000
   6.750   1.0547   0.03170   0.02259  -0.0698   0.5104   1.0000
   7.000   1.0812   0.03187   0.02278  -0.0681   0.4845   1.0000
   7.250   1.1066   0.03215   0.02306  -0.0664   0.4576   1.0000
   7.500   1.1308   0.03262   0.02355  -0.0647   0.4303   1.0000
   7.750   1.1534   0.03323   0.02414  -0.0630   0.4026   1.0000
   8.000   1.1740   0.03405   0.02495  -0.0611   0.3749   1.0000
   8.250   1.1917   0.03516   0.02613  -0.0592   0.3482   1.0000
   8.500   1.2085   0.03644   0.02749  -0.0572   0.3225   1.0000
   8.750   1.2258   0.03783   0.02892  -0.0553   0.2978   1.0000
   9.000   1.2452   0.03916   0.03024  -0.0537   0.2737   1.0000
   9.250   1.2595   0.04085   0.03204  -0.0517   0.2514   1.0000
   9.500   1.2741   0.04270   0.03395  -0.0497   0.2304   1.0000
   9.750   1.2857   0.04477   0.03617  -0.0476   0.2116   1.0000
  10.000   1.3067   0.04667   0.03788  -0.0465   0.1924   1.0000
  10.250   1.3159   0.04937   0.04081  -0.0444   0.1782   1.0000
  10.500   1.3238   0.05192   0.04354  -0.0422   0.1644   1.0000
  10.750   1.3159   0.05567   0.04786  -0.0390   0.1575   1.0000
  11.000   1.3204   0.05920   0.05163  -0.0371   0.1490   1.0000
  11.250   1.3043   0.06320   0.05606  -0.0340   0.1450   1.0000
  11.500   1.3076   0.06617   0.05910  -0.0321   0.1359   1.0000
  11.750   1.2823   0.07041   0.06366  -0.0291   0.1352   1.0000
  12.000   1.2548   0.07513   0.06861  -0.0271   0.1355   1.0000
  12.250   1.2259   0.08063   0.07424  -0.0266   0.1362   1.0000
  12.500   1.1975   0.08700   0.08075  -0.0276   0.1372   1.0000
  12.750   1.1709   0.09422   0.08805  -0.0298   0.1381   1.0000
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