Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

S9000 (9%) (s9000-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: S9000 (9%) (s9000-il)
Reynolds number: 200,000
Max Cl/Cd: 71.01 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s9000-il-200000.txt
Download as CSV file: xf-s9000-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S9000 (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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4413   0.08552   0.08216  -0.0375   1.0000   0.0417
  -8.000  -0.4502   0.08079   0.07746  -0.0419   1.0000   0.0418
  -7.750  -0.4593   0.07483   0.07158  -0.0418   1.0000   0.0426
  -7.500  -0.4553   0.07276   0.06956  -0.0386   1.0000   0.0434
  -7.250  -0.4533   0.07016   0.06700  -0.0377   1.0000   0.0444
  -7.000  -0.4529   0.06691   0.06374  -0.0383   1.0000   0.0453
  -6.750  -0.4528   0.06332   0.06013  -0.0393   1.0000   0.0464
  -6.500  -0.4522   0.05946   0.05622  -0.0403   1.0000   0.0479
  -6.250  -0.4500   0.05540   0.05205  -0.0413   1.0000   0.0499
  -6.000  -0.4451   0.05260   0.04852  -0.0435   1.0000   0.0540
  -5.750  -0.4296   0.03439   0.03092  -0.0394   1.0000   0.0560
  -5.500  -0.4222   0.03190   0.02844  -0.0382   1.0000   0.0574
  -5.250  -0.4133   0.02935   0.02579  -0.0375   1.0000   0.0595
  -5.000  -0.3953   0.02967   0.02436  -0.0416   1.0000   0.0288
  -4.750  -0.3704   0.02446   0.01814  -0.0409   1.0000   0.0227
  -4.500  -0.3480   0.02312   0.01650  -0.0399   1.0000   0.0223
  -4.250  -0.3238   0.02097   0.01401  -0.0394   1.0000   0.0222
  -4.000  -0.2948   0.01834   0.01108  -0.0397   0.9993   0.0230
  -3.750  -0.2548   0.01720   0.00990  -0.0425   0.9953   0.0278
  -3.500  -0.2161   0.01575   0.00832  -0.0445   0.9911   0.0329
  -3.250  -0.1761   0.01460   0.00721  -0.0471   0.9865   0.0490
  -3.000  -0.1354   0.01357   0.00631  -0.0498   0.9821   0.0930
  -2.750  -0.0982   0.01230   0.00577  -0.0525   0.9760   0.2376
  -2.500  -0.0571   0.01148   0.00560  -0.0558   0.9712   0.4121
  -2.250  -0.0239   0.01077   0.00552  -0.0570   0.9631   0.5766
  -2.000   0.0128   0.01035   0.00559  -0.0581   0.9575   0.7294
  -1.750   0.0420   0.01015   0.00551  -0.0574   0.9478   0.8048
  -1.500   0.0747   0.00998   0.00540  -0.0574   0.9409   0.8610
  -1.250   0.1053   0.00980   0.00522  -0.0568   0.9327   0.9063
  -1.000   0.1481   0.00961   0.00496  -0.0589   0.9281   0.9460
  -0.750   0.2008   0.00942   0.00468  -0.0635   0.9216   0.9754
  -0.500   0.2617   0.00917   0.00432  -0.0698   0.9172   0.9941
  -0.250   0.3029   0.00895   0.00403  -0.0725   0.9058   1.0000
   0.000   0.3354   0.00877   0.00377  -0.0733   0.8920   1.0000
   0.250   0.3655   0.00864   0.00355  -0.0735   0.8765   1.0000
   0.500   0.3940   0.00856   0.00337  -0.0734   0.8598   1.0000
   0.750   0.4198   0.00855   0.00327  -0.0727   0.8408   1.0000
   1.000   0.4454   0.00857   0.00320  -0.0720   0.8208   1.0000
   1.250   0.4719   0.00862   0.00313  -0.0714   0.8016   1.0000
   1.500   0.4971   0.00871   0.00313  -0.0707   0.7803   1.0000
   1.750   0.5231   0.00881   0.00312  -0.0701   0.7597   1.0000
   2.000   0.5484   0.00892   0.00317  -0.0693   0.7369   1.0000
   2.250   0.5740   0.00906   0.00319  -0.0686   0.7137   1.0000
   2.500   0.5992   0.00922   0.00324  -0.0679   0.6888   1.0000
   2.750   0.6244   0.00939   0.00332  -0.0672   0.6635   1.0000
   3.000   0.6496   0.00959   0.00344  -0.0665   0.6385   1.0000
   3.250   0.6746   0.00981   0.00355  -0.0658   0.6129   1.0000
   3.500   0.6995   0.01005   0.00369  -0.0650   0.5866   1.0000
   3.750   0.7241   0.01031   0.00386  -0.0643   0.5589   1.0000
   4.000   0.7486   0.01059   0.00406  -0.0636   0.5302   1.0000
   4.250   0.7726   0.01089   0.00426  -0.0628   0.5000   1.0000
   4.500   0.7967   0.01122   0.00449  -0.0620   0.4698   1.0000
   4.750   0.8206   0.01157   0.00475  -0.0613   0.4404   1.0000
   5.000   0.8444   0.01194   0.00506  -0.0606   0.4107   1.0000
   5.250   0.8680   0.01235   0.00538  -0.0598   0.3811   1.0000
   5.500   0.8914   0.01279   0.00573  -0.0591   0.3521   1.0000
   5.750   0.9144   0.01325   0.00611  -0.0583   0.3219   1.0000
   6.000   0.9372   0.01375   0.00653  -0.0575   0.2922   1.0000
   6.250   0.9598   0.01428   0.00698  -0.0568   0.2638   1.0000
   6.500   0.9823   0.01483   0.00747  -0.0560   0.2372   1.0000
   6.750   1.0044   0.01544   0.00800  -0.0552   0.2127   1.0000
   7.000   1.0261   0.01611   0.00862  -0.0543   0.1897   1.0000
   7.250   1.0478   0.01678   0.00928  -0.0535   0.1672   1.0000
   7.500   1.0679   0.01761   0.01000  -0.0524   0.1468   1.0000
   7.750   1.0888   0.01838   0.01079  -0.0515   0.1273   1.0000
   8.000   1.1084   0.01926   0.01164  -0.0503   0.1110   1.0000
   8.250   1.1276   0.02018   0.01253  -0.0492   0.0967   1.0000
   8.500   1.1466   0.02112   0.01352  -0.0480   0.0849   1.0000
   8.750   1.1648   0.02215   0.01460  -0.0467   0.0751   1.0000
   9.000   1.1815   0.02332   0.01580  -0.0453   0.0665   1.0000
   9.250   1.1980   0.02440   0.01690  -0.0439   0.0583   1.0000
   9.500   1.2146   0.02550   0.01815  -0.0424   0.0507   1.0000
   9.750   1.2264   0.02733   0.01999  -0.0405   0.0448   1.0000
  10.000   1.2413   0.02849   0.02133  -0.0388   0.0395   1.0000
  10.250   1.2508   0.03085   0.02367  -0.0369   0.0350   1.0000
  10.500   1.2633   0.03219   0.02531  -0.0348   0.0322   1.0000
  10.750   1.2729   0.03383   0.02710  -0.0326   0.0297   1.0000
  11.000   1.2796   0.03569   0.02902  -0.0305   0.0274   1.0000
  11.250   1.2830   0.03872   0.03229  -0.0282   0.0254   1.0000
  11.500   1.2859   0.04055   0.03440  -0.0257   0.0239   1.0000
  11.750   1.2869   0.04288   0.03696  -0.0235   0.0227   1.0000
  12.000   1.2857   0.04497   0.03922  -0.0216   0.0213   1.0000
  12.250   1.2851   0.04690   0.04119  -0.0203   0.0200   1.0000
  12.500   1.2766   0.05098   0.04543  -0.0192   0.0189   1.0000
  12.750   1.2621   0.05547   0.05022  -0.0185   0.0185   1.0000
  13.000   1.2512   0.05916   0.05419  -0.0186   0.0181   1.0000
  13.250   1.2379   0.06383   0.05913  -0.0194   0.0179   1.0000
  13.500   1.2225   0.06912   0.06466  -0.0212   0.0177   1.0000
  13.750   1.2052   0.07518   0.07097  -0.0239   0.0176   1.0000
  14.000   1.1870   0.08186   0.07786  -0.0274   0.0177   1.0000
  14.250   1.1670   0.08938   0.08560  -0.0319   0.0177   1.0000
  14.500   1.1468   0.09747   0.09387  -0.0369   0.0179   1.0000
  14.750   1.1252   0.10650   0.10307  -0.0427   0.0181   1.0000
  15.000   1.1033   0.11615   0.11285  -0.0489   0.0184   1.0000
<< Back to S9000 (9%) (s9000-il)

Polar data table (+)

Polar graphs


<< Back to S9000 (9%) (s9000-il)