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S9032 (9%) (s9032-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: S9032 (9%) (s9032-il)
Reynolds number: 200,000
Max Cl/Cd: 43.16 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s9032-il-200000.txt
Download as CSV file: xf-s9032-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S9032 (9%)                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.8257   0.07565   0.07196  -0.0134   1.0000   0.0390
 -11.250  -0.8556   0.06662   0.06285  -0.0202   1.0000   0.0383
 -11.000  -0.8838   0.06007   0.05615  -0.0247   1.0000   0.0379
 -10.750  -0.9086   0.05540   0.05131  -0.0256   1.0000   0.0375
 -10.500  -0.9306   0.05134   0.04702  -0.0240   1.0000   0.0373
 -10.250  -0.9431   0.04724   0.04257  -0.0227   1.0000   0.0377
 -10.000  -0.9469   0.04369   0.03863  -0.0212   1.0000   0.0383
  -9.750  -0.9419   0.04145   0.03597  -0.0196   1.0000   0.0392
  -9.500  -0.9396   0.03725   0.03130  -0.0180   1.0000   0.0398
  -9.250  -0.9319   0.03297   0.02663  -0.0167   1.0000   0.0406
  -9.000  -0.9162   0.03041   0.02387  -0.0157   1.0000   0.0417
  -8.750  -0.8973   0.02885   0.02218  -0.0148   1.0000   0.0434
  -8.500  -0.8774   0.02745   0.02059  -0.0139   1.0000   0.0455
  -8.250  -0.8569   0.02577   0.01863  -0.0128   1.0000   0.0473
  -8.000  -0.8354   0.02421   0.01682  -0.0118   1.0000   0.0491
  -7.750  -0.8133   0.02277   0.01513  -0.0108   1.0000   0.0508
  -7.500  -0.7926   0.02079   0.01315  -0.0099   1.0000   0.0542
  -7.250  -0.7698   0.01994   0.01224  -0.0091   1.0000   0.0586
  -6.750  -0.7252   0.01786   0.01005  -0.0072   1.0000   0.0705
  -6.500  -0.7030   0.01685   0.00902  -0.0062   1.0000   0.0786
  -6.250  -0.6791   0.01633   0.00840  -0.0054   1.0000   0.0883
  -6.000  -0.6567   0.01556   0.00769  -0.0045   1.0000   0.1000
  -5.750  -0.6339   0.01489   0.00706  -0.0036   1.0000   0.1127
  -5.500  -0.6108   0.01430   0.00648  -0.0028   1.0000   0.1280
  -5.250  -0.5881   0.01368   0.00596  -0.0019   1.0000   0.1461
  -5.000  -0.5652   0.01313   0.00550  -0.0010   1.0000   0.1682
  -4.750  -0.5425   0.01258   0.00509  -0.0001   1.0000   0.1941
  -4.500  -0.5197   0.01208   0.00470   0.0008   1.0000   0.2236
  -4.250  -0.4968   0.01162   0.00436   0.0017   1.0000   0.2560
  -4.000  -0.4741   0.01118   0.00409   0.0027   1.0000   0.2905
  -3.750  -0.4512   0.01080   0.00385   0.0036   1.0000   0.3299
  -3.500  -0.4286   0.01042   0.00364   0.0046   1.0000   0.3708
  -3.250  -0.4061   0.01008   0.00347   0.0057   1.0000   0.4134
  -3.000  -0.3838   0.00976   0.00334   0.0068   1.0000   0.4585
  -2.750  -0.3618   0.00946   0.00324   0.0080   1.0000   0.5052
  -2.500  -0.3400   0.00919   0.00316   0.0093   1.0000   0.5513
  -2.250  -0.3185   0.00896   0.00312   0.0107   1.0000   0.5959
  -2.000  -0.2973   0.00876   0.00310   0.0122   1.0000   0.6395
  -1.750  -0.2767   0.00859   0.00311   0.0138   1.0000   0.6830
  -1.500  -0.2569   0.00846   0.00316   0.0156   1.0000   0.7269
  -1.250  -0.2382   0.00836   0.00326   0.0177   1.0000   0.7729
  -1.000  -0.2185   0.00831   0.00341   0.0195   0.9993   0.8230
  -0.750  -0.1705   0.00834   0.00358   0.0160   0.9885   0.8733
  -0.500  -0.1164   0.00843   0.00373   0.0113   0.9798   0.9135
  -0.250  -0.0590   0.00850   0.00383   0.0058   0.9711   0.9413
   0.000   0.0000   0.00853   0.00386   0.0000   0.9595   0.9596
   0.250   0.0591   0.00850   0.00383  -0.0058   0.9412   0.9711
   0.500   0.1166   0.00843   0.00373  -0.0113   0.9135   0.9799
   0.750   0.1705   0.00834   0.00358  -0.0160   0.8736   0.9884
   1.000   0.2186   0.00832   0.00341  -0.0195   0.8232   0.9992
   1.250   0.2385   0.00836   0.00326  -0.0177   0.7731   1.0000
   1.500   0.2573   0.00846   0.00316  -0.0157   0.7272   1.0000
   1.750   0.2770   0.00859   0.00312  -0.0139   0.6826   1.0000
   2.000   0.2977   0.00876   0.00310  -0.0123   0.6393   1.0000
   2.250   0.3189   0.00896   0.00312  -0.0108   0.5958   1.0000
   2.500   0.3404   0.00919   0.00316  -0.0094   0.5512   1.0000
   2.750   0.3622   0.00946   0.00324  -0.0081   0.5050   1.0000
   3.000   0.3842   0.00976   0.00334  -0.0069   0.4584   1.0000
   3.250   0.4065   0.01008   0.00347  -0.0058   0.4131   1.0000
   3.500   0.4290   0.01042   0.00364  -0.0047   0.3705   1.0000
   3.750   0.4516   0.01080   0.00385  -0.0037   0.3297   1.0000
   4.000   0.4745   0.01118   0.00409  -0.0028   0.2903   1.0000
   4.250   0.4972   0.01162   0.00437  -0.0018   0.2558   1.0000
   4.500   0.5201   0.01208   0.00470  -0.0009   0.2235   1.0000
   4.750   0.5429   0.01258   0.00509   0.0000   0.1939   1.0000
   5.000   0.5655   0.01313   0.00551   0.0009   0.1681   1.0000
   5.250   0.5884   0.01368   0.00596   0.0018   0.1460   1.0000
   5.500   0.6111   0.01430   0.00648   0.0027   0.1279   1.0000
   5.750   0.6341   0.01489   0.00706   0.0036   0.1127   1.0000
   6.000   0.6568   0.01556   0.00769   0.0045   0.1000   1.0000
   6.250   0.6791   0.01634   0.00840   0.0054   0.0883   1.0000
   6.500   0.7030   0.01685   0.00901   0.0062   0.0786   1.0000
   6.750   0.7251   0.01785   0.01005   0.0072   0.0705   1.0000
   7.000   0.7471   0.01884   0.01099   0.0081   0.0638   1.0000
   7.250   0.7696   0.01992   0.01223   0.0091   0.0586   1.0000
   7.500   0.7924   0.02079   0.01315   0.0099   0.0542   1.0000
   7.750   0.8131   0.02271   0.01507   0.0109   0.0509   1.0000
   8.000   0.8351   0.02421   0.01681   0.0119   0.0491   1.0000
   8.250   0.8566   0.02576   0.01863   0.0129   0.0474   1.0000
   8.500   0.8769   0.02746   0.02058   0.0139   0.0456   1.0000
   8.750   0.8968   0.02886   0.02218   0.0149   0.0434   1.0000
   9.000   0.9158   0.03039   0.02384   0.0158   0.0417   1.0000
   9.250   0.9313   0.03297   0.02663   0.0168   0.0405   1.0000
   9.500   0.9395   0.03712   0.03116   0.0181   0.0398   1.0000
   9.750   0.9412   0.04147   0.03598   0.0197   0.0392   1.0000
  10.000   0.9460   0.04377   0.03869   0.0213   0.0384   1.0000
  10.250   0.9428   0.04714   0.04247   0.0228   0.0377   1.0000
  10.500   0.9303   0.05125   0.04692   0.0242   0.0374   1.0000
  10.750   0.9084   0.05532   0.05122   0.0257   0.0376   1.0000
  11.000   0.8833   0.05994   0.05602   0.0249   0.0378   1.0000
  11.250   0.8559   0.06645   0.06267   0.0205   0.0384   1.0000
  11.500   0.8249   0.07563   0.07194   0.0132   0.0390   1.0000
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