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KENNEDY AND MARSDEN AIRFOIL (kenmar-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: KENNEDY AND MARSDEN AIRFOIL (kenmar-il)
Reynolds number: 200,000
Max Cl/Cd: 17.14 at α=-0.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-kenmar-il-200000-n5.txt
Download as CSV file: xf-kenmar-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: KENNEDY AND MARSDEN AIRFOIL                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000   0.4158   0.11166   0.10377  -0.1521   0.4565   0.0534
 -10.750   0.4212   0.10881   0.10094  -0.1533   0.4562   0.0528
 -10.500   0.4250   0.10572   0.09787  -0.1545   0.4560   0.0523
 -10.250   0.4278   0.10245   0.09462  -0.1558   0.4558   0.0519
  -9.750   0.1481   0.05194   0.04344  -0.1832   0.4572   0.0510
  -9.500   0.1301   0.04850   0.03985  -0.1845   0.4571   0.0510
  -9.250   0.1215   0.04614   0.03737  -0.1848   0.4568   0.0511
  -9.000   0.1176   0.04428   0.03543  -0.1846   0.4566   0.0513
  -8.750   0.1163   0.04272   0.03380  -0.1841   0.4563   0.0514
  -8.500   0.1171   0.04139   0.03239  -0.1832   0.4560   0.0516
  -8.250   0.1191   0.04022   0.03116  -0.1820   0.4557   0.0518
  -8.000   0.1213   0.03922   0.03010  -0.1805   0.4554   0.0520
  -7.750   0.1230   0.03845   0.02928  -0.1786   0.4551   0.0522
  -7.500   0.1237   0.03783   0.02861  -0.1762   0.4547   0.0524
  -7.250   0.1250   0.03729   0.02803  -0.1737   0.4542   0.0526
  -7.000   0.1312   0.03671   0.02739  -0.1719   0.4536   0.0529
  -6.750   0.1396   0.03617   0.02680  -0.1703   0.4531   0.0533
  -6.500   0.1497   0.03568   0.02624  -0.1689   0.4526   0.0538
  -6.250   0.1614   0.03523   0.02573  -0.1676   0.4522   0.0542
  -6.000   0.1746   0.03481   0.02524  -0.1664   0.4517   0.0547
  -5.750   0.1888   0.03445   0.02480  -0.1652   0.4513   0.0551
  -5.500   0.2040   0.03414   0.02442  -0.1639   0.4509   0.0554
  -5.250   0.2196   0.03385   0.02417  -0.1624   0.4504   0.0557
  -5.000   0.2354   0.03363   0.02399  -0.1610   0.4500   0.0561
  -4.750   0.2513   0.03346   0.02385  -0.1596   0.4495   0.0564
  -4.500   0.2674   0.03332   0.02374  -0.1582   0.4491   0.0568
  -4.250   0.2837   0.03321   0.02365  -0.1568   0.4486   0.0572
  -4.000   0.3003   0.03310   0.02357  -0.1555   0.4481   0.0577
  -3.750   0.3176   0.03299   0.02346  -0.1542   0.4476   0.0582
  -3.500   0.3356   0.03286   0.02333  -0.1531   0.4469   0.0588
  -3.250   0.3542   0.03275   0.02322  -0.1520   0.4463   0.0594
  -3.000   0.3732   0.03268   0.02314  -0.1511   0.4458   0.0600
  -2.750   0.3924   0.03267   0.02313  -0.1502   0.4453   0.0607
  -2.500   0.4120   0.03271   0.02315  -0.1494   0.4449   0.0613
  -2.250   0.4322   0.03270   0.02320  -0.1488   0.4444   0.0621
  -2.000   0.4536   0.03275   0.02329  -0.1485   0.4440   0.0629
  -1.750   0.4767   0.03284   0.02341  -0.1484   0.4435   0.0639
  -1.500   0.5015   0.03296   0.02353  -0.1486   0.4430   0.0653
  -1.250   0.5276   0.03313   0.02368  -0.1490   0.4424   0.0671
  -1.000   0.5549   0.03338   0.02393  -0.1498   0.4418   0.0687
  -0.750   0.5810   0.03390   0.02448  -0.1505   0.4410   0.0706
  -0.500   0.5890   0.03438   0.02508  -0.1484   0.4404   0.0720
  -0.250   0.5849   0.03512   0.02595  -0.1444   0.4397   0.0732
   0.000   0.5702   0.03668   0.02771  -0.1397   0.4384   0.0739
   0.250   0.3154   0.05464   0.04640  -0.1214   0.4254   0.0661
   0.500   0.3397   0.05541   0.04714  -0.1224   0.4248   0.0677
   0.750   0.3675   0.05599   0.04776  -0.1238   0.4242   0.0695
   1.000   0.3952   0.05659   0.04837  -0.1251   0.4238   0.0716
   1.250   0.4230   0.05718   0.04894  -0.1263   0.4233   0.0740
   2.250   0.2913   0.08289   0.07500  -0.1273   0.3972   0.0723
   2.500   0.3155   0.08399   0.07609  -0.1285   0.3963   0.0747
   2.750   0.3420   0.08501   0.07715  -0.1300   0.3956   0.0776
   3.000   0.3685   0.08593   0.07807  -0.1312   0.3950   0.0816
   3.250   0.3965   0.08683   0.07901  -0.1327   0.3944   0.0875
   3.500   0.4259   0.08762   0.07987  -0.1342   0.3940   0.0978
   3.750   0.4579   0.08841   0.08079  -0.1363   0.3936   0.1227
   4.250   0.4366   0.09771   0.09033  -0.1383   0.3829   0.1463
   4.500   0.4759   0.09893   0.09195  -0.1425   0.3821   0.2382
   4.750   0.5237   0.10044   0.09402  -0.1486   0.3815   0.3750
   5.000   0.5539   0.10150   0.09586  -0.1501   0.3809   0.5590
   5.250   0.5721   0.10220   0.09660  -0.1491   0.3805   0.5948
   5.750   0.5547   0.11045   0.10497  -0.1493   0.3705   0.6155
   6.000   0.5732   0.11134   0.10582  -0.1488   0.3695   0.6367
   6.250   0.5906   0.11226   0.10669  -0.1479   0.3687   0.6571
   6.500   0.5969   0.11250   0.10699  -0.1442   0.3681   0.6679
   6.750   0.6178   0.11333   0.10775  -0.1438   0.3676   0.6819
   7.000   0.6274   0.11358   0.10803  -0.1408   0.3671   0.6875
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