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S9033 (7.5%) (s9033-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: S9033 (7.5%) (s9033-il)
Reynolds number: 200,000
Max Cl/Cd: 42.95 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s9033-il-200000-n5.txt
Download as CSV file: xf-s9033-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.9095   0.06715   0.06356  -0.0042   1.0000   0.0181
 -11.250  -0.9551   0.05388   0.05003  -0.0167   1.0000   0.0171
 -11.000  -0.9783   0.04870   0.04461  -0.0192   1.0000   0.0171
 -10.750  -0.9930   0.04487   0.04051  -0.0186   1.0000   0.0173
 -10.500  -0.9953   0.04164   0.03697  -0.0181   1.0000   0.0180
 -10.250  -0.9931   0.03842   0.03339  -0.0173   1.0000   0.0186
 -10.000  -0.9858   0.03551   0.03008  -0.0165   1.0000   0.0192
  -9.750  -0.9742   0.03299   0.02716  -0.0156   1.0000   0.0197
  -9.500  -0.9611   0.03045   0.02425  -0.0147   1.0000   0.0204
  -9.250  -0.9450   0.02852   0.02214  -0.0140   1.0000   0.0215
  -9.000  -0.9253   0.02732   0.02082  -0.0134   1.0000   0.0226
  -8.750  -0.9053   0.02590   0.01920  -0.0126   1.0000   0.0235
  -8.500  -0.8846   0.02446   0.01756  -0.0119   1.0000   0.0244
  -8.250  -0.8632   0.02312   0.01601  -0.0111   1.0000   0.0253
  -8.000  -0.8411   0.02191   0.01461  -0.0104   1.0000   0.0264
  -7.750  -0.8180   0.02098   0.01345  -0.0097   1.0000   0.0277
  -7.500  -0.7964   0.01969   0.01209  -0.0090   1.0000   0.0295
  -7.250  -0.7732   0.01880   0.01113  -0.0084   1.0000   0.0313
  -7.000  -0.7495   0.01799   0.01022  -0.0078   1.0000   0.0334
  -6.750  -0.7255   0.01723   0.00935  -0.0071   1.0000   0.0359
  -6.500  -0.7016   0.01645   0.00847  -0.0065   1.0000   0.0390
  -6.250  -0.6773   0.01577   0.00775  -0.0059   1.0000   0.0436
  -6.000  -0.6522   0.01528   0.00716  -0.0054   1.0000   0.0492
  -5.750  -0.6276   0.01468   0.00658  -0.0049   1.0000   0.0570
  -5.500  -0.6026   0.01418   0.00606  -0.0043   1.0000   0.0646
  -5.250  -0.5772   0.01376   0.00560  -0.0038   1.0000   0.0736
  -5.000  -0.5521   0.01332   0.00517  -0.0034   1.0000   0.0848
  -4.750  -0.5268   0.01290   0.00479  -0.0029   1.0000   0.0979
  -4.500  -0.5016   0.01250   0.00443  -0.0024   1.0000   0.1127
  -4.250  -0.4763   0.01212   0.00410  -0.0019   1.0000   0.1295
  -4.000  -0.4510   0.01175   0.00379  -0.0013   1.0000   0.1474
  -3.750  -0.4257   0.01143   0.00350  -0.0008   1.0000   0.1665
  -3.500  -0.4005   0.01110   0.00326  -0.0003   1.0000   0.1895
  -3.250  -0.3754   0.01077   0.00304   0.0003   1.0000   0.2166
  -3.000  -0.3503   0.01047   0.00284   0.0009   1.0000   0.2449
  -2.750  -0.3255   0.01017   0.00266   0.0015   1.0000   0.2774
  -2.500  -0.3009   0.00986   0.00251   0.0021   1.0000   0.3155
  -2.250  -0.2765   0.00955   0.00239   0.0028   1.0000   0.3588
  -2.000  -0.2523   0.00926   0.00229   0.0036   1.0000   0.4044
  -1.750  -0.2282   0.00899   0.00220   0.0044   1.0000   0.4486
  -1.500  -0.2044   0.00874   0.00215   0.0052   1.0000   0.4949
  -1.250  -0.1809   0.00848   0.00212   0.0062   1.0000   0.5450
  -1.000  -0.1508   0.00822   0.00212   0.0058   0.9934   0.6043
  -0.750  -0.1142   0.00796   0.00215   0.0042   0.9749   0.6709
  -0.500  -0.0787   0.00773   0.00217   0.0030   0.9492   0.7327
  -0.250  -0.0395   0.00755   0.00219   0.0014   0.9109   0.7951
   0.000   0.0000   0.00747   0.00220   0.0000   0.8572   0.8573
   0.250   0.0395   0.00755   0.00219  -0.0014   0.7950   0.9109
   0.500   0.0786   0.00773   0.00217  -0.0030   0.7328   0.9490
   0.750   0.1142   0.00796   0.00215  -0.0042   0.6710   0.9749
   1.000   0.1507   0.00823   0.00212  -0.0058   0.6040   0.9933
   1.250   0.1810   0.00848   0.00212  -0.0062   0.5450   1.0000
   1.500   0.2044   0.00874   0.00215  -0.0052   0.4950   1.0000
   1.750   0.2283   0.00899   0.00220  -0.0044   0.4486   1.0000
   2.000   0.2524   0.00926   0.00229  -0.0036   0.4041   1.0000
   2.250   0.2766   0.00955   0.00239  -0.0028   0.3585   1.0000
   2.500   0.3010   0.00986   0.00251  -0.0021   0.3154   1.0000
   2.750   0.3256   0.01017   0.00266  -0.0015   0.2772   1.0000
   3.000   0.3504   0.01047   0.00284  -0.0009   0.2448   1.0000
   3.250   0.3755   0.01077   0.00304  -0.0003   0.2163   1.0000
   3.500   0.4005   0.01110   0.00326   0.0003   0.1895   1.0000
   3.750   0.4257   0.01143   0.00350   0.0008   0.1665   1.0000
   4.000   0.4511   0.01175   0.00380   0.0013   0.1474   1.0000
   4.250   0.4763   0.01212   0.00410   0.0018   0.1294   1.0000
   4.500   0.5016   0.01250   0.00443   0.0024   0.1126   1.0000
   4.750   0.5269   0.01290   0.00479   0.0029   0.0978   1.0000
   5.000   0.5521   0.01332   0.00517   0.0033   0.0848   1.0000
   5.250   0.5772   0.01376   0.00560   0.0038   0.0737   1.0000
   5.500   0.6025   0.01418   0.00606   0.0043   0.0646   1.0000
   5.750   0.6276   0.01468   0.00658   0.0049   0.0571   1.0000
   6.000   0.6521   0.01528   0.00716   0.0054   0.0492   1.0000
   6.250   0.6773   0.01577   0.00774   0.0059   0.0436   1.0000
   6.500   0.7015   0.01645   0.00847   0.0065   0.0390   1.0000
   6.750   0.7254   0.01724   0.00935   0.0071   0.0360   1.0000
   7.000   0.7494   0.01799   0.01022   0.0078   0.0334   1.0000
   7.250   0.7731   0.01880   0.01112   0.0084   0.0313   1.0000
   7.500   0.7963   0.01968   0.01208   0.0090   0.0295   1.0000
   7.750   0.8178   0.02097   0.01344   0.0098   0.0277   1.0000
   8.000   0.8410   0.02191   0.01460   0.0104   0.0264   1.0000
   8.250   0.8630   0.02312   0.01600   0.0112   0.0253   1.0000
   8.500   0.8844   0.02445   0.01755   0.0119   0.0244   1.0000
   8.750   0.9050   0.02589   0.01919   0.0127   0.0235   1.0000
   9.000   0.9250   0.02731   0.02081   0.0134   0.0226   1.0000
   9.250   0.9447   0.02854   0.02217   0.0140   0.0216   1.0000
   9.500   0.9609   0.03045   0.02425   0.0148   0.0204   1.0000
   9.750   0.9739   0.03298   0.02716   0.0156   0.0197   1.0000
  10.000   0.9854   0.03552   0.03009   0.0165   0.0193   1.0000
  10.250   0.9927   0.03842   0.03338   0.0174   0.0186   1.0000
  10.500   0.9959   0.04147   0.03679   0.0181   0.0179   1.0000
  10.750   0.9934   0.04476   0.04040   0.0186   0.0173   1.0000
  11.000   0.9801   0.04844   0.04435   0.0192   0.0170   1.0000
  11.250   0.9548   0.05391   0.05005   0.0167   0.0172   1.0000
  11.500   0.9114   0.06674   0.06315   0.0045   0.0181   1.0000
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