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S9033 (7.5%) (s9033-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S9033 (7.5%) (s9033-il)
Reynolds number: 50,000
Max Cl/Cd: 23.46 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s9033-il-50000-n5.txt
Download as CSV file: xf-s9033-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.7350   0.08850   0.08142   0.0049   1.0000   0.0591
  -9.500  -0.7493   0.08019   0.07315  -0.0014   1.0000   0.0587
  -9.250  -0.7692   0.07310   0.06607  -0.0067   1.0000   0.0582
  -9.000  -0.7867   0.06674   0.05958  -0.0099   1.0000   0.0579
  -8.750  -0.7989   0.06066   0.05323  -0.0122   1.0000   0.0579
  -8.500  -0.8047   0.05495   0.04711  -0.0134   1.0000   0.0584
  -8.250  -0.8044   0.04966   0.04125  -0.0140   1.0000   0.0598
  -8.000  -0.7964   0.04555   0.03664  -0.0139   1.0000   0.0623
  -7.750  -0.7796   0.04350   0.03451  -0.0135   1.0000   0.0659
  -7.500  -0.7640   0.04037   0.03095  -0.0130   1.0000   0.0692
  -7.250  -0.7465   0.03695   0.02692  -0.0124   1.0000   0.0723
  -7.000  -0.7265   0.03447   0.02415  -0.0117   1.0000   0.0765
  -6.750  -0.7052   0.03280   0.02226  -0.0112   1.0000   0.0840
  -6.500  -0.6832   0.03090   0.02010  -0.0105   1.0000   0.0910
  -6.250  -0.6598   0.02912   0.01800  -0.0097   1.0000   0.0995
  -6.000  -0.6372   0.02784   0.01668  -0.0091   1.0000   0.1112
  -5.750  -0.6136   0.02645   0.01521  -0.0084   1.0000   0.1224
  -5.500  -0.5900   0.02531   0.01397  -0.0077   1.0000   0.1382
  -5.250  -0.5657   0.02414   0.01266  -0.0070   1.0000   0.1540
  -5.000  -0.5417   0.02309   0.01164  -0.0064   1.0000   0.1729
  -4.750  -0.5174   0.02215   0.01068  -0.0057   1.0000   0.1966
  -4.500  -0.4930   0.02124   0.00984  -0.0052   1.0000   0.2228
  -4.250  -0.4683   0.02041   0.00909  -0.0047   1.0000   0.2555
  -4.000  -0.4441   0.01964   0.00841  -0.0041   1.0000   0.2933
  -3.750  -0.4206   0.01892   0.00785  -0.0033   1.0000   0.3369
  -3.500  -0.3975   0.01825   0.00737  -0.0023   1.0000   0.3852
  -3.250  -0.3747   0.01763   0.00696  -0.0012   1.0000   0.4394
  -3.000  -0.3524   0.01705   0.00663   0.0003   1.0000   0.4984
  -2.750  -0.3308   0.01651   0.00634   0.0020   1.0000   0.5621
  -2.500  -0.3095   0.01603   0.00612   0.0040   1.0000   0.6297
  -2.250  -0.2878   0.01561   0.00595   0.0062   1.0000   0.6996
  -2.000  -0.2626   0.01527   0.00581   0.0080   1.0000   0.7728
  -1.750  -0.2256   0.01505   0.00566   0.0076   1.0000   0.8508
  -1.500  -0.1725   0.01491   0.00545   0.0035   1.0000   0.9235
  -1.250  -0.1131   0.01475   0.00511  -0.0026   1.0000   0.9813
  -1.000  -0.0775   0.01456   0.00480  -0.0048   1.0000   1.0000
  -0.750  -0.0586   0.01445   0.00461  -0.0036   1.0000   1.0000
  -0.500  -0.0392   0.01438   0.00448  -0.0025   1.0000   1.0000
  -0.250  -0.0197   0.01434   0.00440  -0.0012   1.0000   1.0000
   0.000   0.0000   0.01432   0.00438   0.0000   1.0000   1.0000
   0.250   0.0197   0.01434   0.00440   0.0012   1.0000   1.0000
   0.500   0.0392   0.01438   0.00448   0.0025   1.0000   1.0000
   0.750   0.0586   0.01445   0.00461   0.0036   1.0000   1.0000
   1.000   0.0775   0.01456   0.00480   0.0048   1.0000   1.0000
   1.250   0.1132   0.01475   0.00511   0.0026   0.9812   1.0000
   1.500   0.1725   0.01491   0.00545  -0.0035   0.9234   1.0000
   1.750   0.2256   0.01505   0.00566  -0.0076   0.8509   1.0000
   2.000   0.2626   0.01527   0.00579  -0.0080   0.7728   1.0000
   2.250   0.2878   0.01561   0.00595  -0.0062   0.6996   1.0000
   2.500   0.3095   0.01603   0.00612  -0.0040   0.6297   1.0000
   2.750   0.3308   0.01651   0.00634  -0.0020   0.5621   1.0000
   3.250   0.3747   0.01763   0.00696   0.0012   0.4395   1.0000
   3.500   0.3975   0.01825   0.00737   0.0023   0.3851   1.0000
   3.750   0.4206   0.01892   0.00786   0.0032   0.3368   1.0000
   4.000   0.4441   0.01964   0.00841   0.0041   0.2933   1.0000
   4.250   0.4683   0.02041   0.00909   0.0047   0.2556   1.0000
   4.500   0.4930   0.02124   0.00984   0.0052   0.2228   1.0000
   4.750   0.5174   0.02214   0.01068   0.0057   0.1967   1.0000
   5.000   0.5417   0.02309   0.01163   0.0064   0.1729   1.0000
   5.250   0.5657   0.02413   0.01266   0.0070   0.1540   1.0000
   5.500   0.5899   0.02531   0.01397   0.0078   0.1381   1.0000
   5.750   0.6135   0.02645   0.01521   0.0084   0.1224   1.0000
   6.000   0.6371   0.02784   0.01667   0.0091   0.1111   1.0000
   6.250   0.6598   0.02912   0.01800   0.0098   0.0996   1.0000
   6.500   0.6831   0.03089   0.02009   0.0105   0.0910   1.0000
   6.750   0.7052   0.03280   0.02225   0.0112   0.0840   1.0000
   7.000   0.7264   0.03446   0.02414   0.0118   0.0764   1.0000
   7.250   0.7465   0.03694   0.02691   0.0124   0.0724   1.0000
   7.500   0.7639   0.04036   0.03094   0.0130   0.0692   1.0000
   7.750   0.7795   0.04350   0.03450   0.0135   0.0659   1.0000
   8.000   0.7963   0.04555   0.03665   0.0139   0.0623   1.0000
   8.250   0.8044   0.04965   0.04123   0.0140   0.0598   1.0000
   8.500   0.8046   0.05495   0.04711   0.0135   0.0584   1.0000
   8.750   0.7988   0.06067   0.05323   0.0122   0.0579   1.0000
   9.000   0.7867   0.06676   0.05959   0.0099   0.0579   1.0000
   9.250   0.7693   0.07311   0.06608   0.0066   0.0581   1.0000
   9.500   0.7492   0.08027   0.07323   0.0013   0.0586   1.0000
   9.750   0.7352   0.08855   0.08147  -0.0050   0.0591   1.0000
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