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

S4310 (s4310-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S4310 (s4310-il)
Reynolds number: 100,000
Max Cl/Cd: 56.31 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4310-il-100000.txt
Download as CSV file: xf-s4310-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4310                                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2522   0.10407   0.10003  -0.0390   1.0000   0.0858
  -9.000  -0.2748   0.10421   0.10029  -0.0363   1.0000   0.0859
  -8.750  -0.2963   0.10416   0.10036  -0.0337   1.0000   0.0860
  -8.500  -0.2678   0.09815   0.09434  -0.0286   1.0000   0.0889
  -8.250  -0.2941   0.09640   0.09212  -0.0378   1.0000   0.0891
  -8.000  -0.3037   0.09527   0.09108  -0.0343   1.0000   0.0905
  -7.750  -0.3225   0.09487   0.09080  -0.0302   1.0000   0.0916
  -7.500  -0.3434   0.09457   0.09061  -0.0262   1.0000   0.0923
  -7.250  -0.3647   0.09418   0.09032  -0.0226   1.0000   0.0933
  -7.000  -0.3774   0.09292   0.08914  -0.0217   0.9981   0.0946
  -6.750  -0.3619   0.08608   0.08221  -0.0476   0.9824   0.1005
  -6.500  -0.3398   0.08260   0.07881  -0.0398   0.9801   0.1035
  -6.250  -0.3150   0.07841   0.07457  -0.0459   0.9725   0.1107
  -6.000  -0.2974   0.07279   0.06887  -0.0563   0.9621   0.1168
  -5.750  -0.2672   0.06909   0.06513  -0.0598   0.9572   0.1247
  -5.500  -0.2511   0.06463   0.06058  -0.0654   0.9468   0.1325
  -5.250  -0.2268   0.06050   0.05628  -0.0717   0.9388   0.1458
  -5.000  -0.2024   0.05727   0.05297  -0.0743   0.9315   0.1611
  -4.750  -0.1777   0.05425   0.04989  -0.0764   0.9248   0.1770
  -4.500  -0.1528   0.05122   0.04678  -0.0786   0.9172   0.1930
  -4.250  -0.1209   0.04821   0.04364  -0.0818   0.9117   0.2136
  -4.000  -0.0725   0.03368   0.02629  -0.0891   0.9034   0.0724
  -3.750  -0.0316   0.03023   0.02261  -0.0924   0.9000   0.0759
  -3.500  -0.0084   0.02866   0.02067  -0.0915   0.8912   0.0766
  -3.250   0.0319   0.02674   0.01836  -0.0932   0.8867   0.0785
  -3.000   0.0611   0.02585   0.01720  -0.0931   0.8794   0.0843
  -2.750   0.0946   0.02448   0.01576  -0.0938   0.8733   0.0900
  -2.500   0.1361   0.02334   0.01452  -0.0955   0.8697   0.1004
  -2.250   0.1538   0.02282   0.01412  -0.0938   0.8595   0.1159
  -2.000   0.1886   0.02108   0.01302  -0.0945   0.8554   0.2133
  -1.750   0.2015   0.01991   0.01315  -0.0922   0.8457   0.5054
  -1.500   0.2825   0.01841   0.01261  -0.0994   0.8446   1.0000
  -1.250   0.3114   0.01848   0.01237  -0.0994   0.8380   1.0000
  -1.000   0.3325   0.01872   0.01238  -0.0982   0.8287   1.0000
  -0.750   0.3556   0.01896   0.01241  -0.0973   0.8203   1.0000
  -0.500   0.3834   0.01903   0.01227  -0.0970   0.8131   1.0000
  -0.250   0.4045   0.01935   0.01243  -0.0958   0.8039   1.0000
   0.000   0.4348   0.01931   0.01223  -0.0957   0.7976   1.0000
   0.250   0.4551   0.01968   0.01247  -0.0944   0.7876   1.0000
   0.500   0.4868   0.01955   0.01219  -0.0944   0.7820   1.0000
   0.750   0.5069   0.01994   0.01250  -0.0931   0.7715   1.0000
   1.000   0.5396   0.01972   0.01214  -0.0930   0.7664   1.0000
   1.250   0.5598   0.02012   0.01247  -0.0918   0.7554   1.0000
   1.500   0.5848   0.02026   0.01254  -0.0910   0.7467   1.0000
   1.750   0.6136   0.02017   0.01237  -0.0905   0.7392   1.0000
   2.000   0.6364   0.02045   0.01260  -0.0895   0.7290   1.0000
   2.250   0.6682   0.02016   0.01221  -0.0892   0.7229   1.0000
   2.500   0.6903   0.02046   0.01251  -0.0881   0.7117   1.0000
   2.750   0.7161   0.02053   0.01254  -0.0874   0.7025   1.0000
   3.000   0.7456   0.02035   0.01230  -0.0868   0.6945   1.0000
   3.250   0.7690   0.02056   0.01251  -0.0859   0.6834   1.0000
   3.500   0.7963   0.02052   0.01246  -0.0852   0.6742   1.0000
   3.750   0.8252   0.02035   0.01225  -0.0847   0.6651   1.0000
   4.000   0.8492   0.02050   0.01241  -0.0837   0.6533   1.0000
   4.250   0.8750   0.02053   0.01243  -0.0829   0.6422   1.0000
   4.500   0.9040   0.02033   0.01222  -0.0824   0.6322   1.0000
   4.750   0.9315   0.02022   0.01209  -0.0817   0.6208   1.0000
   5.000   0.9562   0.02027   0.01216  -0.0808   0.6076   1.0000
   5.250   0.9815   0.02030   0.01223  -0.0799   0.5943   1.0000
   5.500   1.0070   0.02030   0.01224  -0.0791   0.5806   1.0000
   5.750   1.0326   0.02031   0.01225  -0.0783   0.5663   1.0000
   6.000   1.0580   0.02032   0.01227  -0.0774   0.5514   1.0000
   6.250   1.0832   0.02035   0.01231  -0.0765   0.5359   1.0000
   6.500   1.1084   0.02040   0.01234  -0.0757   0.5198   1.0000
   6.750   1.1331   0.02050   0.01242  -0.0748   0.5029   1.0000
   7.000   1.1542   0.02079   0.01276  -0.0735   0.4837   1.0000
   7.250   1.1767   0.02104   0.01302  -0.0724   0.4647   1.0000
   7.500   1.1999   0.02131   0.01322  -0.0714   0.4461   1.0000
   7.750   1.2194   0.02177   0.01371  -0.0700   0.4258   1.0000
   8.000   1.2396   0.02223   0.01414  -0.0687   0.4057   1.0000
   8.250   1.2600   0.02276   0.01461  -0.0675   0.3865   1.0000
   8.500   1.2771   0.02342   0.01532  -0.0659   0.3662   1.0000
   8.750   1.2953   0.02411   0.01596  -0.0645   0.3472   1.0000
   9.000   1.3135   0.02487   0.01663  -0.0632   0.3290   1.0000
   9.250   1.3285   0.02573   0.01754  -0.0614   0.3108   1.0000
   9.500   1.3436   0.02663   0.01847  -0.0598   0.2935   1.0000
   9.750   1.3586   0.02758   0.01941  -0.0581   0.2771   1.0000
  10.000   1.3730   0.02858   0.02041  -0.0565   0.2617   1.0000
  10.250   1.3863   0.02963   0.02147  -0.0547   0.2470   1.0000
  10.500   1.3985   0.03074   0.02261  -0.0529   0.2331   1.0000
  10.750   1.4098   0.03192   0.02383  -0.0509   0.2201   1.0000
  11.000   1.4193   0.03312   0.02512  -0.0488   0.2080   1.0000
  11.250   1.4286   0.03437   0.02638  -0.0467   0.1968   1.0000
  11.500   1.4405   0.03567   0.02764  -0.0450   0.1858   1.0000
  11.750   1.4449   0.03699   0.02909  -0.0426   0.1760   1.0000
  12.000   1.4492   0.03855   0.03080  -0.0403   0.1668   1.0000
  12.250   1.4599   0.04007   0.03230  -0.0388   0.1576   1.0000
  12.500   1.4620   0.04167   0.03404  -0.0367   0.1495   1.0000
  12.750   1.4654   0.04355   0.03605  -0.0348   0.1417   1.0000
  13.000   1.4754   0.04504   0.03743  -0.0337   0.1326   1.0000
  13.250   1.4640   0.04736   0.04014  -0.0312   0.1271   1.0000
  13.500   1.4650   0.04904   0.04170  -0.0299   0.1189   1.0000
  13.750   1.4514   0.05176   0.04476  -0.0283   0.1133   1.0000
  14.000   1.4472   0.05390   0.04679  -0.0274   0.1059   1.0000
  14.250   1.4324   0.05722   0.05043  -0.0268   0.1005   1.0000
  14.500   1.4261   0.05987   0.05298  -0.0265   0.0937   1.0000
  14.750   1.4125   0.06386   0.05732  -0.0266   0.0887   1.0000
  15.000   1.4086   0.06683   0.06015  -0.0267   0.0820   1.0000
  15.250   1.3919   0.07176   0.06547  -0.0277   0.0773   1.0000
  15.500   1.3827   0.07576   0.06944  -0.0286   0.0714   1.0000
  15.750   1.3662   0.08138   0.07532  -0.0303   0.0661   1.0000
  16.000   1.3544   0.08628   0.08022  -0.0320   0.0605   1.0000
  16.250   1.3379   0.09254   0.08669  -0.0342   0.0556   1.0000
  16.500   1.3263   0.09808   0.09230  -0.0364   0.0511   1.0000
<< Back to S4310 (s4310-il)

Polar data table (+)

Polar graphs


<< Back to S4310 (s4310-il)