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

K3311 (original) (k3311-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: K3311 (original) (k3311-il)
Reynolds number: 100,000
Max Cl/Cd: 56.92 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-k3311-il-100000-n5.txt
Download as CSV file: xf-k3311-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: K3311  (original)                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3713   0.09781   0.09289  -0.0405   1.0000   0.0698
  -9.000  -0.3906   0.09453   0.08976  -0.0450   1.0000   0.0710
  -8.750  -0.3923   0.08525   0.08048  -0.0462   1.0000   0.0463
  -8.500  -0.3882   0.08276   0.07802  -0.0442   1.0000   0.0448
  -8.250  -0.3955   0.07955   0.07491  -0.0439   1.0000   0.0435
  -8.000  -0.4106   0.07634   0.07182  -0.0436   1.0000   0.0424
  -7.750  -0.4273   0.07217   0.06775  -0.0448   1.0000   0.0413
  -7.250  -0.4624   0.05666   0.05172  -0.0533   0.9949   0.0361
  -7.000  -0.4419   0.05068   0.04538  -0.0585   0.9862   0.0359
  -6.750  -0.4209   0.04494   0.03907  -0.0629   0.9766   0.0369
  -6.500  -0.3956   0.04194   0.03600  -0.0654   0.9686   0.0385
  -6.250  -0.3678   0.03788   0.03144  -0.0682   0.9611   0.0388
  -6.000  -0.3407   0.03435   0.02737  -0.0698   0.9522   0.0389
  -5.750  -0.3112   0.03170   0.02430  -0.0713   0.9444   0.0397
  -5.500  -0.2788   0.02968   0.02190  -0.0731   0.9371   0.0418
  -5.250  -0.2475   0.02759   0.01939  -0.0742   0.9294   0.0428
  -5.000  -0.2149   0.02566   0.01707  -0.0752   0.9221   0.0433
  -4.750  -0.1838   0.02410   0.01521  -0.0758   0.9141   0.0438
  -4.500  -0.1509   0.02274   0.01358  -0.0767   0.9068   0.0445
  -4.250  -0.1200   0.02179   0.01241  -0.0772   0.8984   0.0464
  -4.000  -0.0879   0.02059   0.01116  -0.0780   0.8912   0.0480
  -3.750  -0.0595   0.01968   0.01021  -0.0781   0.8818   0.0489
  -3.500  -0.0274   0.01885   0.00932  -0.0789   0.8747   0.0502
  -3.250  -0.0010   0.01826   0.00867  -0.0785   0.8640   0.0516
  -3.000   0.0277   0.01772   0.00803  -0.0786   0.8548   0.0535
  -2.750   0.0571   0.01726   0.00742  -0.0787   0.8459   0.0559
  -2.500   0.0837   0.01688   0.00695  -0.0784   0.8352   0.0596
  -2.250   0.1119   0.01648   0.00652  -0.0784   0.8258   0.0694
  -2.000   0.1395   0.01596   0.00608  -0.0782   0.8162   0.0962
  -1.750   0.1616   0.01473   0.00581  -0.0777   0.8059   0.3294
  -1.500   0.1843   0.01395   0.00587  -0.0766   0.7969   0.5671
  -1.250   0.2091   0.01365   0.00580  -0.0754   0.7875   0.6580
  -1.000   0.2333   0.01341   0.00576  -0.0739   0.7777   0.7411
  -0.750   0.2647   0.01314   0.00564  -0.0736   0.7697   0.8300
  -0.500   0.3415   0.01287   0.00541  -0.0829   0.7608   0.9791
  -0.250   0.3773   0.01292   0.00526  -0.0847   0.7510   1.0000
   0.000   0.4019   0.01299   0.00515  -0.0841   0.7413   1.0000
   0.250   0.4250   0.01310   0.00513  -0.0833   0.7299   1.0000
   0.500   0.4491   0.01321   0.00510  -0.0825   0.7190   1.0000
   0.750   0.4739   0.01331   0.00507  -0.0819   0.7082   1.0000
   1.000   0.4991   0.01342   0.00503  -0.0812   0.6974   1.0000
   1.250   0.5236   0.01355   0.00507  -0.0806   0.6863   1.0000
   1.500   0.5488   0.01370   0.00513  -0.0800   0.6763   1.0000
   1.750   0.5752   0.01385   0.00515  -0.0796   0.6677   1.0000
   2.000   0.5997   0.01404   0.00530  -0.0789   0.6574   1.0000
   2.250   0.6249   0.01423   0.00545  -0.0784   0.6480   1.0000
   2.500   0.6508   0.01442   0.00557  -0.0780   0.6392   1.0000
   2.750   0.6749   0.01463   0.00579  -0.0773   0.6286   1.0000
   3.000   0.6996   0.01483   0.00600  -0.0767   0.6189   1.0000
   3.250   0.7251   0.01501   0.00615  -0.0762   0.6096   1.0000
   3.500   0.7490   0.01520   0.00637  -0.0754   0.5983   1.0000
   3.750   0.7733   0.01539   0.00657  -0.0747   0.5872   1.0000
   4.000   0.7980   0.01557   0.00676  -0.0740   0.5762   1.0000
   4.250   0.8230   0.01575   0.00692  -0.0734   0.5659   1.0000
   4.500   0.8469   0.01598   0.00720  -0.0727   0.5545   1.0000
   4.750   0.8713   0.01622   0.00750  -0.0720   0.5437   1.0000
   5.000   0.8959   0.01646   0.00776  -0.0713   0.5334   1.0000
   5.250   0.9200   0.01672   0.00806  -0.0706   0.5222   1.0000
   5.500   0.9434   0.01701   0.00843  -0.0698   0.5104   1.0000
   5.750   0.9667   0.01730   0.00881  -0.0689   0.4979   1.0000
   6.000   0.9894   0.01759   0.00915  -0.0679   0.4835   1.0000
   6.250   1.0109   0.01787   0.00946  -0.0667   0.4659   1.0000
   6.500   1.0318   0.01816   0.00978  -0.0654   0.4475   1.0000
   6.750   1.0527   0.01850   0.01021  -0.0642   0.4301   1.0000
   7.000   1.0735   0.01886   0.01068  -0.0630   0.4136   1.0000
   7.250   1.0938   0.01924   0.01117  -0.0617   0.3963   1.0000
   7.500   1.1139   0.01965   0.01168  -0.0604   0.3797   1.0000
   7.750   1.1318   0.02012   0.01220  -0.0587   0.3592   1.0000
   8.000   1.1440   0.02075   0.01271  -0.0562   0.3233   1.0000
   8.250   1.1514   0.02166   0.01336  -0.0532   0.2756   1.0000
   8.500   1.1570   0.02276   0.01419  -0.0501   0.2274   1.0000
   8.750   1.1636   0.02390   0.01515  -0.0473   0.1882   1.0000
   9.000   1.1662   0.02520   0.01624  -0.0440   0.1473   1.0000
   9.250   1.1653   0.02676   0.01756  -0.0404   0.1114   1.0000
   9.500   1.1645   0.02847   0.01909  -0.0371   0.0807   1.0000
   9.750   1.1623   0.03038   0.02085  -0.0340   0.0549   1.0000
  10.000   1.1602   0.03237   0.02275  -0.0312   0.0438   1.0000
  10.250   1.1604   0.03429   0.02474  -0.0289   0.0382   1.0000
  10.500   1.1600   0.03636   0.02689  -0.0269   0.0347   1.0000
  10.750   1.1562   0.03882   0.02941  -0.0250   0.0325   1.0000
  11.000   1.1570   0.04101   0.03178  -0.0236   0.0311   1.0000
  11.250   1.1566   0.04342   0.03436  -0.0224   0.0294   1.0000
  11.500   1.1561   0.04595   0.03702  -0.0214   0.0280   1.0000
  11.750   1.1552   0.04861   0.03979  -0.0207   0.0267   1.0000
  12.000   1.1516   0.05166   0.04292  -0.0202   0.0255   1.0000
  12.250   1.1507   0.05452   0.04591  -0.0197   0.0244   1.0000
  12.500   1.1528   0.05713   0.04869  -0.0192   0.0237   1.0000
  12.750   1.1552   0.05979   0.05149  -0.0186   0.0229   1.0000
  13.000   1.1587   0.06239   0.05423  -0.0181   0.0223   1.0000
  13.250   1.1625   0.06503   0.05700  -0.0177   0.0217   1.0000
  13.500   1.1659   0.06781   0.05992  -0.0174   0.0210   1.0000
  13.750   1.1677   0.07081   0.06303  -0.0174   0.0203   1.0000
  14.000   1.1692   0.07389   0.06622  -0.0175   0.0197   1.0000
  14.250   1.1709   0.07705   0.06945  -0.0175   0.0191   1.0000
  14.500   1.1695   0.08081   0.07338  -0.0180   0.0185   1.0000
  14.750   1.1653   0.08502   0.07785  -0.0190   0.0181   1.0000
  15.000   1.1607   0.08945   0.08251  -0.0202   0.0180   1.0000
  15.250   1.1533   0.09444   0.08778  -0.0219   0.0178   1.0000
  15.500   1.1445   0.09977   0.09333  -0.0240   0.0177   1.0000
  15.750   1.1337   0.10565   0.09945  -0.0266   0.0176   1.0000
  16.000   1.1214   0.11204   0.10606  -0.0298   0.0176   1.0000
  16.250   1.1068   0.11919   0.11343  -0.0337   0.0175   1.0000
  16.500   1.0922   0.12666   0.12110  -0.0380   0.0176   1.0000
  16.750   1.0749   0.13519   0.12980  -0.0433   0.0177   1.0000
  17.000   1.0582   0.14412   0.13889  -0.0489   0.0178   1.0000
  17.250   1.0394   0.15424   0.14915  -0.0553   0.0180   1.0000
  17.500   1.0205   0.16521   0.16021  -0.0622   0.0183   1.0000
<< Back to K3311 (original) (k3311-il)

Polar data table (+)

Polar graphs


<< Back to K3311 (original) (k3311-il)