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S9033 (7.5%) (s9033-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S9033 (7.5%) (s9033-il)
Reynolds number: 100,000
Max Cl/Cd: 32.28 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s9033-il-100000-n5.txt
Download as CSV file: xf-s9033-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S9033 (7.5%)                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.7723   0.08292   0.07796   0.0056   1.0000   0.0339
 -10.000  -0.8241   0.06531   0.06036  -0.0098   1.0000   0.0325
  -9.750  -0.8586   0.05781   0.05265  -0.0141   1.0000   0.0320
  -9.500  -0.8762   0.05187   0.04634  -0.0155   1.0000   0.0320
  -9.250  -0.8819   0.04688   0.04093  -0.0157   1.0000   0.0324
  -9.000  -0.8795   0.04260   0.03617  -0.0154   1.0000   0.0331
  -8.750  -0.8709   0.03896   0.03205  -0.0149   1.0000   0.0342
  -8.500  -0.8578   0.03600   0.02856  -0.0142   1.0000   0.0361
  -8.250  -0.8413   0.03346   0.02547  -0.0134   1.0000   0.0376
  -8.000  -0.8237   0.03083   0.02261  -0.0127   1.0000   0.0390
  -7.750  -0.8034   0.02901   0.02063  -0.0120   1.0000   0.0406
  -7.500  -0.7821   0.02736   0.01878  -0.0113   1.0000   0.0427
  -7.250  -0.7600   0.02576   0.01694  -0.0105   1.0000   0.0452
  -7.000  -0.7369   0.02439   0.01525  -0.0098   1.0000   0.0486
  -6.750  -0.7149   0.02315   0.01402  -0.0092   1.0000   0.0531
  -6.500  -0.6914   0.02209   0.01282  -0.0085   1.0000   0.0586
  -6.250  -0.6685   0.02091   0.01152  -0.0077   1.0000   0.0639
  -6.000  -0.6445   0.02010   0.01062  -0.0071   1.0000   0.0724
  -5.750  -0.6209   0.01927   0.00979  -0.0065   1.0000   0.0817
  -5.500  -0.5969   0.01849   0.00898  -0.0059   1.0000   0.0923
  -5.250  -0.5726   0.01780   0.00827  -0.0053   1.0000   0.1051
  -5.000  -0.5483   0.01714   0.00759  -0.0047   1.0000   0.1197
  -4.750  -0.5238   0.01652   0.00699  -0.0041   1.0000   0.1364
  -4.500  -0.4991   0.01594   0.00641  -0.0035   1.0000   0.1543
  -4.250  -0.4746   0.01538   0.00594  -0.0029   1.0000   0.1766
  -4.000  -0.4500   0.01486   0.00548  -0.0024   1.0000   0.2026
  -3.750  -0.4254   0.01438   0.00510  -0.0018   1.0000   0.2316
  -3.500  -0.4008   0.01392   0.00476  -0.0011   1.0000   0.2661
  -3.250  -0.3765   0.01347   0.00447  -0.0005   1.0000   0.3058
  -3.000  -0.3523   0.01304   0.00421   0.0002   1.0000   0.3503
  -2.750  -0.3282   0.01262   0.00398   0.0010   1.0000   0.3988
  -2.500  -0.3043   0.01223   0.00380   0.0019   1.0000   0.4497
  -2.250  -0.2806   0.01186   0.00365   0.0029   1.0000   0.5034
  -2.000  -0.2570   0.01151   0.00354   0.0040   1.0000   0.5616
  -1.750  -0.2338   0.01118   0.00344   0.0053   1.0000   0.6230
  -1.500  -0.2111   0.01088   0.00339   0.0069   1.0000   0.6863
  -1.250  -0.1883   0.01062   0.00337   0.0085   1.0000   0.7515
  -1.000  -0.1619   0.01042   0.00338   0.0096   1.0000   0.8210
  -0.750  -0.1216   0.01033   0.00342   0.0078   1.0000   0.8952
  -0.500  -0.0709   0.01029   0.00341   0.0035   1.0000   0.9568
  -0.250  -0.0197   0.01026   0.00335  -0.0013   1.0000   0.9990
   0.000   0.0000   0.01025   0.00333   0.0000   1.0000   1.0000
   0.250   0.0198   0.01026   0.00335   0.0013   0.9989   1.0000
   0.500   0.0710   0.01029   0.00341  -0.0035   0.9568   1.0000
   0.750   0.1216   0.01033   0.00342  -0.0079   0.8950   1.0000
   1.000   0.1620   0.01042   0.00338  -0.0096   0.8209   1.0000
   1.250   0.1883   0.01062   0.00337  -0.0085   0.7514   1.0000
   1.500   0.2112   0.01088   0.00339  -0.0069   0.6864   1.0000
   1.750   0.2339   0.01118   0.00344  -0.0053   0.6228   1.0000
   2.000   0.2571   0.01151   0.00354  -0.0040   0.5615   1.0000
   2.250   0.2807   0.01186   0.00365  -0.0029   0.5034   1.0000
   2.500   0.3044   0.01223   0.00380  -0.0020   0.4497   1.0000
   2.750   0.3283   0.01262   0.00398  -0.0011   0.3987   1.0000
   3.000   0.3523   0.01303   0.00422  -0.0003   0.3504   1.0000
   3.250   0.3766   0.01347   0.00447   0.0005   0.3059   1.0000
   3.500   0.4009   0.01392   0.00476   0.0011   0.2661   1.0000
   3.750   0.4254   0.01438   0.00510   0.0017   0.2317   1.0000
   4.000   0.4501   0.01486   0.00548   0.0023   0.2025   1.0000
   4.250   0.4747   0.01538   0.00594   0.0029   0.1766   1.0000
   4.500   0.4992   0.01594   0.00641   0.0035   0.1543   1.0000
   4.750   0.5238   0.01652   0.00699   0.0041   0.1365   1.0000
   5.000   0.5483   0.01714   0.00759   0.0047   0.1197   1.0000
   5.250   0.5726   0.01780   0.00827   0.0053   0.1051   1.0000
   5.500   0.5968   0.01849   0.00897   0.0059   0.0922   1.0000
   5.750   0.6208   0.01927   0.00979   0.0065   0.0817   1.0000
   6.000   0.6445   0.02010   0.01062   0.0071   0.0723   1.0000
   6.250   0.6684   0.02091   0.01152   0.0077   0.0639   1.0000
   6.500   0.6914   0.02209   0.01282   0.0085   0.0586   1.0000
   6.750   0.7148   0.02316   0.01403   0.0092   0.0532   1.0000
   7.000   0.7368   0.02439   0.01525   0.0098   0.0487   1.0000
   7.250   0.7599   0.02576   0.01693   0.0106   0.0452   1.0000
   7.500   0.7819   0.02736   0.01878   0.0113   0.0427   1.0000
   7.750   0.8033   0.02901   0.02062   0.0120   0.0406   1.0000
   8.000   0.8235   0.03082   0.02259   0.0127   0.0391   1.0000
   8.250   0.8411   0.03345   0.02545   0.0134   0.0376   1.0000
   8.500   0.8576   0.03598   0.02854   0.0142   0.0361   1.0000
   8.750   0.8707   0.03895   0.03204   0.0149   0.0342   1.0000
   9.000   0.8793   0.04259   0.03616   0.0155   0.0331   1.0000
   9.250   0.8818   0.04686   0.04090   0.0158   0.0324   1.0000
   9.500   0.8761   0.05184   0.04631   0.0155   0.0320   1.0000
   9.750   0.8588   0.05776   0.05259   0.0141   0.0320   1.0000
  10.000   0.8241   0.06533   0.06038   0.0098   0.0325   1.0000
  10.250   0.7722   0.08308   0.07811  -0.0057   0.0339   1.0000
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