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

S9037 (9%) (s9037-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: S9037 (9%) (s9037-il)
Reynolds number: 1,000,000
Max Cl/Cd: 110.09 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s9037-il-1000000-n5.txt
Download as CSV file: xf-s9037-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S9037 (9%)                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3607   0.10120   0.09953  -0.0284   1.0000   0.0040
  -9.500  -0.3587   0.09739   0.09574  -0.0297   1.0000   0.0041
  -9.250  -0.3593   0.09334   0.09172  -0.0312   1.0000   0.0046
  -9.000  -0.3552   0.09071   0.08910  -0.0320   1.0000   0.0047
  -8.750  -0.3547   0.08721   0.08563  -0.0331   1.0000   0.0048
  -8.250  -0.3405   0.08092   0.07937  -0.0374   0.9872   0.0051
  -8.000  -0.3234   0.07579   0.07424  -0.0443   0.9784   0.0052
  -7.750  -0.3031   0.07043   0.06886  -0.0526   0.9654   0.0055
  -7.500  -0.2920   0.06339   0.06176  -0.0627   0.9396   0.0051
  -7.250  -0.2948   0.05550   0.05375  -0.0706   0.9136   0.0048
  -7.000  -0.2870   0.05052   0.04866  -0.0748   0.8985   0.0049
  -6.750  -0.2755   0.04600   0.04402  -0.0780   0.8861   0.0052
  -6.250  -0.2729   0.02078   0.01739  -0.0832   0.8610   0.0042
  -6.000  -0.2535   0.01725   0.01332  -0.0827   0.8523   0.0041
  -5.750  -0.2304   0.01525   0.01093  -0.0823   0.8434   0.0041
  -5.500  -0.2057   0.01375   0.00913  -0.0819   0.8338   0.0041
  -5.250  -0.1803   0.01262   0.00775  -0.0815   0.8243   0.0040
  -5.000  -0.1544   0.01168   0.00659  -0.0811   0.8143   0.0040
  -4.750  -0.1280   0.01091   0.00565  -0.0808   0.8045   0.0040
  -4.500  -0.1013   0.01029   0.00487  -0.0806   0.7951   0.0040
  -4.250  -0.0745   0.00978   0.00424  -0.0803   0.7851   0.0041
  -4.000  -0.0475   0.00934   0.00368  -0.0801   0.7742   0.0041
  -3.750  -0.0203   0.00896   0.00320  -0.0799   0.7629   0.0041
  -3.500   0.0070   0.00865   0.00279  -0.0797   0.7511   0.0042
  -3.250   0.0345   0.00840   0.00244  -0.0795   0.7391   0.0043
  -3.000   0.0620   0.00821   0.00215  -0.0793   0.7272   0.0043
  -2.500   0.1172   0.00782   0.00161  -0.0790   0.7037   0.0056
  -2.250   0.1450   0.00770   0.00143  -0.0789   0.6922   0.0078
  -2.000   0.1726   0.00756   0.00129  -0.0788   0.6807   0.0173
  -1.750   0.2002   0.00744   0.00119  -0.0787   0.6679   0.0313
  -1.500   0.2276   0.00731   0.00110  -0.0786   0.6538   0.0589
  -1.000   0.2820   0.00693   0.00097  -0.0785   0.6243   0.1742
  -0.500   0.3368   0.00671   0.00092  -0.0784   0.5957   0.2792
  -0.250   0.3641   0.00663   0.00091  -0.0784   0.5815   0.3289
   0.000   0.3914   0.00652   0.00092  -0.0783   0.5676   0.3921
   0.250   0.4184   0.00638   0.00094  -0.0783   0.5527   0.4740
   0.500   0.4453   0.00626   0.00097  -0.0782   0.5371   0.5566
   0.750   0.4716   0.00614   0.00102  -0.0779   0.5185   0.6496
   1.000   0.4970   0.00599   0.00109  -0.0775   0.4989   0.7532
   1.250   0.5205   0.00584   0.00117  -0.0764   0.4814   0.8567
   1.500   0.5435   0.00576   0.00124  -0.0750   0.4652   0.9541
   1.750   0.5815   0.00587   0.00127  -0.0773   0.4490   0.9957
   2.000   0.6096   0.00601   0.00133  -0.0774   0.4330   1.0000
   2.250   0.6361   0.00618   0.00141  -0.0771   0.4145   1.0000
   2.500   0.6625   0.00637   0.00149  -0.0769   0.3940   1.0000
   2.750   0.6888   0.00657   0.00159  -0.0766   0.3743   1.0000
   3.000   0.7154   0.00674   0.00168  -0.0764   0.3584   1.0000
   3.250   0.7421   0.00691   0.00180  -0.0762   0.3440   1.0000
   3.500   0.7686   0.00709   0.00191  -0.0760   0.3284   1.0000
   3.750   0.7950   0.00729   0.00203  -0.0758   0.3126   1.0000
   4.000   0.8215   0.00747   0.00216  -0.0756   0.2991   1.0000
   4.250   0.8477   0.00770   0.00232  -0.0753   0.2817   1.0000
   4.500   0.8732   0.00799   0.00250  -0.0750   0.2590   1.0000
   4.750   0.8989   0.00825   0.00268  -0.0747   0.2400   1.0000
   5.000   0.9248   0.00848   0.00287  -0.0745   0.2260   1.0000
   5.250   0.9506   0.00873   0.00306  -0.0742   0.2113   1.0000
   5.500   0.9758   0.00904   0.00328  -0.0738   0.1935   1.0000
   5.750   1.0012   0.00931   0.00350  -0.0735   0.1796   1.0000
   6.000   1.0267   0.00957   0.00373  -0.0732   0.1679   1.0000
   6.250   1.0514   0.00992   0.00400  -0.0728   0.1516   1.0000
   6.500   1.0757   0.01029   0.00429  -0.0723   0.1328   1.0000
   6.750   1.1001   0.01064   0.00458  -0.0719   0.1183   1.0000
   7.000   1.1244   0.01099   0.00489  -0.0714   0.1060   1.0000
   7.250   1.1484   0.01137   0.00522  -0.0709   0.0935   1.0000
   7.500   1.1715   0.01182   0.00559  -0.0703   0.0784   1.0000
   7.750   1.1945   0.01226   0.00597  -0.0697   0.0660   1.0000
   8.000   1.2179   0.01266   0.00634  -0.0691   0.0575   1.0000
   8.250   1.2407   0.01309   0.00676  -0.0685   0.0495   1.0000
   8.500   1.2626   0.01360   0.00722  -0.0677   0.0393   1.0000
   8.750   1.2839   0.01413   0.00770  -0.0669   0.0303   1.0000
   9.000   1.3056   0.01462   0.00817  -0.0660   0.0250   1.0000
   9.250   1.3268   0.01512   0.00867  -0.0652   0.0201   1.0000
   9.500   1.3468   0.01570   0.00923  -0.0642   0.0151   1.0000
   9.750   1.3664   0.01628   0.00983  -0.0631   0.0112   1.0000
  10.000   1.3843   0.01697   0.01050  -0.0618   0.0066   1.0000
  10.250   1.4017   0.01767   0.01122  -0.0604   0.0040   1.0000
  10.500   1.4188   0.01833   0.01192  -0.0589   0.0029   1.0000
  10.750   1.4360   0.01893   0.01257  -0.0575   0.0026   1.0000
  11.000   1.4506   0.01954   0.01324  -0.0556   0.0023   1.0000
  11.250   1.4625   0.02023   0.01400  -0.0533   0.0021   1.0000
  11.500   1.4742   0.02094   0.01478  -0.0511   0.0020   1.0000
  11.750   1.4845   0.02176   0.01569  -0.0488   0.0018   1.0000
  12.000   1.4940   0.02266   0.01667  -0.0466   0.0017   1.0000
  12.250   1.5036   0.02358   0.01768  -0.0445   0.0016   1.0000
  12.500   1.5128   0.02457   0.01874  -0.0425   0.0016   1.0000
  12.750   1.5208   0.02567   0.01994  -0.0406   0.0016   1.0000
  13.000   1.5280   0.02689   0.02125  -0.0387   0.0015   1.0000
  13.250   1.5346   0.02821   0.02266  -0.0370   0.0015   1.0000
  13.500   1.5395   0.02973   0.02428  -0.0354   0.0014   1.0000
  13.750   1.5433   0.03142   0.02607  -0.0338   0.0013   1.0000
  14.000   1.5468   0.03323   0.02798  -0.0325   0.0013   1.0000
  14.250   1.5478   0.03536   0.03023  -0.0314   0.0013   1.0000
  14.500   1.5488   0.03761   0.03260  -0.0305   0.0013   1.0000
  14.750   1.5480   0.04019   0.03529  -0.0298   0.0012   1.0000
  15.000   1.5456   0.04306   0.03829  -0.0294   0.0012   1.0000
  15.250   1.5438   0.04603   0.04136  -0.0294   0.0012   1.0000
  15.500   1.5388   0.04955   0.04501  -0.0296   0.0011   1.0000
  15.750   1.5326   0.05341   0.04900  -0.0303   0.0011   1.0000
  16.000   1.5238   0.05789   0.05361  -0.0314   0.0011   1.0000
  16.250   1.5161   0.06242   0.05827  -0.0327   0.0011   1.0000
  16.500   1.5064   0.06751   0.06348  -0.0346   0.0010   1.0000
  16.750   1.4931   0.07344   0.06956  -0.0370   0.0010   1.0000
  17.000   1.4776   0.08001   0.07628  -0.0399   0.0010   1.0000
  17.250   1.4613   0.08700   0.08342  -0.0432   0.0010   1.0000
  17.500   1.4480   0.09368   0.09022  -0.0465   0.0010   1.0000
  17.750   1.4257   0.10231   0.09901  -0.0509   0.0010   1.0000
  18.000   1.4064   0.11061   0.10745  -0.0553   0.0010   1.0000
<< Back to S9037 (9%) (s9037-il)

Polar data table (+)

Polar graphs


<< Back to S9037 (9%) (s9037-il)