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S9026 (9.5%) (s9026-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: S9026 (9.5%) (s9026-il)
Reynolds number: 200,000
Max Cl/Cd: 44.28 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s9026-il-200000.txt
Download as CSV file: xf-s9026-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S9026 (9.5%)                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.5562   0.12940   0.12595   0.0156   1.0000   0.0741
 -12.000  -0.8774   0.06960   0.06569  -0.0231   1.0000   0.0351
 -11.750  -0.8990   0.06399   0.05991  -0.0273   1.0000   0.0350
 -11.250  -0.9386   0.05549   0.05104  -0.0291   1.0000   0.0347
 -11.000  -0.9584   0.05211   0.04744  -0.0270   1.0000   0.0348
 -10.500  -0.9851   0.04325   0.03787  -0.0232   1.0000   0.0352
 -10.250  -0.9860   0.03899   0.03330  -0.0217   1.0000   0.0360
 -10.000  -0.9727   0.03729   0.03156  -0.0208   1.0000   0.0377
  -9.750  -0.9582   0.03581   0.02995  -0.0197   1.0000   0.0395
  -9.500  -0.9456   0.03356   0.02738  -0.0183   1.0000   0.0409
  -9.250  -0.9313   0.03124   0.02471  -0.0169   1.0000   0.0421
  -9.000  -0.9139   0.02968   0.02283  -0.0156   1.0000   0.0439
  -8.750  -0.8971   0.02736   0.02018  -0.0143   1.0000   0.0456
  -8.500  -0.8778   0.02520   0.01793  -0.0134   1.0000   0.0477
  -8.250  -0.8565   0.02393   0.01657  -0.0125   1.0000   0.0499
  -8.000  -0.8348   0.02273   0.01521  -0.0115   1.0000   0.0527
  -7.750  -0.8121   0.02192   0.01417  -0.0106   1.0000   0.0558
  -7.500  -0.7918   0.02017   0.01246  -0.0096   1.0000   0.0603
  -7.250  -0.7695   0.01929   0.01152  -0.0086   1.0000   0.0653
  -7.000  -0.7484   0.01810   0.01030  -0.0075   1.0000   0.0714
  -6.750  -0.7258   0.01746   0.00960  -0.0066   1.0000   0.0796
  -6.500  -0.7044   0.01661   0.00879  -0.0056   1.0000   0.0893
  -6.250  -0.6826   0.01586   0.00805  -0.0045   1.0000   0.0998
  -6.000  -0.6605   0.01521   0.00741  -0.0035   1.0000   0.1119
  -5.750  -0.6384   0.01460   0.00686  -0.0025   1.0000   0.1264
  -5.500  -0.6163   0.01405   0.00637  -0.0015   1.0000   0.1440
  -5.250  -0.5942   0.01351   0.00588  -0.0005   1.0000   0.1652
  -5.000  -0.5725   0.01296   0.00545   0.0006   1.0000   0.1896
  -4.750  -0.5508   0.01244   0.00507   0.0017   1.0000   0.2169
  -4.500  -0.5289   0.01198   0.00473   0.0027   1.0000   0.2481
  -4.250  -0.5071   0.01153   0.00443   0.0038   1.0000   0.2824
  -4.000  -0.4854   0.01113   0.00418   0.0049   1.0000   0.3191
  -3.750  -0.4638   0.01076   0.00396   0.0060   1.0000   0.3568
  -3.500  -0.4423   0.01042   0.00379   0.0072   1.0000   0.3978
  -3.250  -0.4213   0.01010   0.00364   0.0085   1.0000   0.4413
  -3.000  -0.4005   0.00980   0.00354   0.0098   1.0000   0.4859
  -2.750  -0.3801   0.00954   0.00347   0.0113   1.0000   0.5313
  -2.500  -0.3598   0.00933   0.00344   0.0128   1.0000   0.5754
  -2.250  -0.3399   0.00915   0.00344   0.0144   1.0000   0.6193
  -2.000  -0.3204   0.00903   0.00349   0.0161   1.0000   0.6624
  -1.750  -0.3016   0.00895   0.00358   0.0179   1.0000   0.7049
  -1.500  -0.2751   0.00892   0.00372   0.0181   0.9970   0.7491
  -1.250  -0.2324   0.00890   0.00385   0.0154   0.9873   0.7946
  -1.000  -0.1895   0.00888   0.00396   0.0129   0.9772   0.8342
  -0.750  -0.1438   0.00888   0.00403   0.0099   0.9680   0.8677
  -0.500  -0.0985   0.00888   0.00409   0.0071   0.9576   0.8966
  -0.250  -0.0497   0.00891   0.00415   0.0037   0.9473   0.9184
   0.000   0.0000   0.00892   0.00417   0.0000   0.9353   0.9353
   0.250   0.0497   0.00891   0.00415  -0.0037   0.9183   0.9472
   0.500   0.0985   0.00888   0.00409  -0.0071   0.8965   0.9576
   0.750   0.1439   0.00888   0.00403  -0.0099   0.8678   0.9680
   1.000   0.1895   0.00888   0.00396  -0.0129   0.8341   0.9771
   1.250   0.2324   0.00890   0.00386  -0.0154   0.7948   0.9873
   1.500   0.2751   0.00892   0.00372  -0.0181   0.7490   0.9970
   1.750   0.3017   0.00895   0.00358  -0.0179   0.7047   1.0000
   2.000   0.3206   0.00903   0.00349  -0.0161   0.6623   1.0000
   2.250   0.3401   0.00916   0.00344  -0.0144   0.6191   1.0000
   2.500   0.3600   0.00933   0.00344  -0.0128   0.5752   1.0000
   2.750   0.3802   0.00955   0.00347  -0.0113   0.5311   1.0000
   3.000   0.4007   0.00980   0.00354  -0.0099   0.4859   1.0000
   3.250   0.4214   0.01010   0.00364  -0.0085   0.4411   1.0000
   3.500   0.4425   0.01042   0.00379  -0.0073   0.3978   1.0000
   3.750   0.4639   0.01076   0.00396  -0.0061   0.3567   1.0000
   4.000   0.4856   0.01113   0.00418  -0.0049   0.3191   1.0000
   4.250   0.5073   0.01153   0.00443  -0.0038   0.2824   1.0000
   4.500   0.5290   0.01198   0.00473  -0.0027   0.2481   1.0000
   4.750   0.5509   0.01244   0.00507  -0.0017   0.2168   1.0000
   5.000   0.5727   0.01296   0.00546  -0.0006   0.1895   1.0000
   5.250   0.5943   0.01352   0.00588   0.0004   0.1651   1.0000
   5.500   0.6164   0.01405   0.00637   0.0015   0.1440   1.0000
   5.750   0.6385   0.01460   0.00686   0.0025   0.1264   1.0000
   6.000   0.6606   0.01520   0.00741   0.0035   0.1119   1.0000
   6.250   0.6827   0.01586   0.00805   0.0045   0.0998   1.0000
   6.500   0.7044   0.01661   0.00879   0.0055   0.0893   1.0000
   6.750   0.7258   0.01746   0.00961   0.0066   0.0796   1.0000
   7.000   0.7484   0.01810   0.01030   0.0075   0.0713   1.0000
   7.250   0.7695   0.01929   0.01152   0.0086   0.0653   1.0000
   7.500   0.7918   0.02017   0.01246   0.0096   0.0602   1.0000
   7.750   0.8120   0.02189   0.01415   0.0106   0.0558   1.0000
   8.000   0.8347   0.02271   0.01520   0.0116   0.0526   1.0000
   8.250   0.8564   0.02392   0.01655   0.0125   0.0499   1.0000
   8.500   0.8776   0.02521   0.01793   0.0134   0.0477   1.0000
   8.750   0.8970   0.02736   0.02017   0.0143   0.0456   1.0000
   9.000   0.9137   0.02971   0.02285   0.0156   0.0439   1.0000
   9.250   0.9311   0.03123   0.02471   0.0169   0.0422   1.0000
   9.500   0.9454   0.03354   0.02736   0.0183   0.0408   1.0000
   9.750   0.9582   0.03575   0.02989   0.0197   0.0394   1.0000
  10.000   0.9721   0.03740   0.03169   0.0208   0.0378   1.0000
  10.250   0.9857   0.03899   0.03331   0.0217   0.0361   1.0000
  10.500   0.9851   0.04321   0.03783   0.0233   0.0352   1.0000
  11.000   0.9589   0.05209   0.04741   0.0270   0.0348   1.0000
  11.250   0.9390   0.05572   0.05126   0.0291   0.0348   1.0000
  11.500   0.7253   0.10013   0.09649  -0.0029   0.0488   1.0000
  11.750   0.7621   0.09253   0.08894   0.0023   0.0432   1.0000
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