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LNV109A (lnv109a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: LNV109A (lnv109a-il)
Reynolds number: 1,000,000
Max Cl/Cd: 151.49 at α=10°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-lnv109a-il-1000000.txt
Download as CSV file: xf-lnv109a-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LNV109A                                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.000  -0.2103   0.08722   0.08358  -0.0007   0.4339   0.0298
  -6.750  -0.2030   0.08483   0.08120  -0.0017   0.4331   0.0301
  -6.500  -0.1967   0.08244   0.07882  -0.0025   0.4323   0.0305
  -6.250  -0.1938   0.08002   0.07642  -0.0033   0.4315   0.0313
  -5.750  -0.1955   0.06958   0.06598  -0.0151   0.4305   0.0326
  -5.500  -0.1796   0.06748   0.06387  -0.0163   0.4294   0.0327
  -5.250  -0.1626   0.06549   0.06187  -0.0176   0.4281   0.0328
  -5.000  -0.1448   0.06336   0.05973  -0.0195   0.4265   0.0330
  -4.750  -0.1257   0.06099   0.05735  -0.0217   0.4262   0.0333
  -4.500  -0.1052   0.05842   0.05477  -0.0243   0.4259   0.0337
  -4.250  -0.0735   0.04677   0.04289  -0.0389   0.4257   0.0363
  -4.000  -0.0515   0.04507   0.04116  -0.0398   0.4252   0.0365
  -3.750  -0.0275   0.04351   0.03958  -0.0407   0.4245   0.0367
  -3.500  -0.0022   0.01740   0.01147  -0.0538   0.4246   0.0364
  -3.250   0.0254   0.01639   0.01034  -0.0537   0.4238   0.0368
  -3.000   0.0538   0.01592   0.00984  -0.0535   0.4229   0.0371
  -2.750   0.0824   0.01557   0.00944  -0.0533   0.4220   0.0374
  -2.500   0.1110   0.01514   0.00895  -0.0531   0.4211   0.0378
  -2.250   0.1396   0.01462   0.00833  -0.0529   0.4201   0.0382
  -2.000   0.1683   0.01408   0.00769  -0.0527   0.4191   0.0388
  -1.750   0.1970   0.01360   0.00709  -0.0525   0.4181   0.0393
  -1.500   0.2260   0.01328   0.00668  -0.0523   0.4170   0.0399
  -1.250   0.2551   0.01305   0.00636  -0.0520   0.4159   0.0403
  -1.000   0.2835   0.01236   0.00558  -0.0518   0.4150   0.0408
  -0.750   0.3122   0.01203   0.00525  -0.0516   0.4140   0.0412
  -0.500   0.3411   0.01185   0.00505  -0.0514   0.4129   0.0417
  -0.250   0.3700   0.01171   0.00489  -0.0512   0.4116   0.0423
   0.000   0.3986   0.01168   0.00484  -0.0510   0.4096   0.0429
   0.250   0.4275   0.01157   0.00471  -0.0508   0.4085   0.0436
   0.500   0.4566   0.01141   0.00454  -0.0506   0.4079   0.0443
   0.750   0.4857   0.01127   0.00440  -0.0504   0.4072   0.0449
   1.000   0.5144   0.01097   0.00413  -0.0503   0.4064   0.0458
   1.250   0.5434   0.01084   0.00403  -0.0501   0.4055   0.0467
   1.500   0.5724   0.01073   0.00394  -0.0499   0.4044   0.0476
   1.750   0.6015   0.01063   0.00385  -0.0497   0.4032   0.0486
   2.000   0.6306   0.01055   0.00377  -0.0496   0.4020   0.0495
   2.250   0.6594   0.01039   0.00363  -0.0494   0.4008   0.0510
   2.500   0.6884   0.01033   0.00359  -0.0493   0.3997   0.0526
   2.750   0.7175   0.01029   0.00355  -0.0491   0.3986   0.0544
   3.000   0.7464   0.01020   0.00347  -0.0490   0.3974   0.0567
   3.250   0.7753   0.01017   0.00345  -0.0488   0.3961   0.0594
   3.500   0.8041   0.01018   0.00347  -0.0487   0.3945   0.0629
   3.750   0.8326   0.01034   0.00363  -0.0486   0.3925   0.0675
   4.000   0.8616   0.01026   0.00362  -0.0485   0.3918   0.0770
   4.250   0.8904   0.01014   0.00364  -0.0484   0.3908   0.1090
   4.500   0.9187   0.00988   0.00373  -0.0483   0.3896   0.2569
   4.750   0.9510   0.00845   0.00391  -0.0494   0.3883   1.0000
   5.000   0.9799   0.00850   0.00394  -0.0493   0.3869   1.0000
   5.250   1.0087   0.00854   0.00396  -0.0492   0.3853   1.0000
   5.500   1.0375   0.00858   0.00398  -0.0491   0.3838   1.0000
   5.750   1.0662   0.00862   0.00400  -0.0490   0.3823   1.0000
   6.000   1.0949   0.00868   0.00404  -0.0489   0.3807   1.0000
   6.250   1.1232   0.00881   0.00413  -0.0488   0.3787   1.0000
   6.500   1.1516   0.00895   0.00427  -0.0487   0.3768   1.0000
   6.750   1.1802   0.00900   0.00434  -0.0486   0.3755   1.0000
   7.000   1.2088   0.00905   0.00442  -0.0486   0.3738   1.0000
   7.250   1.2373   0.00911   0.00449  -0.0485   0.3719   1.0000
   7.500   1.2658   0.00917   0.00456  -0.0484   0.3699   1.0000
   7.750   1.2942   0.00923   0.00462  -0.0484   0.3679   1.0000
   8.000   1.3224   0.00932   0.00470  -0.0483   0.3657   1.0000
   8.250   1.3502   0.00950   0.00485  -0.0482   0.3628   1.0000
   8.500   1.3784   0.00957   0.00497  -0.0482   0.3611   1.0000
   8.750   1.4067   0.00965   0.00510  -0.0482   0.3587   1.0000
   9.000   1.4349   0.00969   0.00516  -0.0482   0.3548   1.0000
   9.250   1.4624   0.00980   0.00520  -0.0481   0.3481   1.0000
   9.500   1.4906   0.00985   0.00530  -0.0481   0.3414   1.0000
   9.750   1.5177   0.01004   0.00546  -0.0480   0.3355   1.0000
  10.000   1.5452   0.01020   0.00564  -0.0480   0.3309   1.0000
  10.250   1.5724   0.01038   0.00585  -0.0480   0.3254   1.0000
  10.500   1.5989   0.01065   0.00610  -0.0479   0.3196   1.0000
  10.750   1.6260   0.01085   0.00633  -0.0478   0.3139   1.0000
  11.000   1.6517   0.01119   0.00665  -0.0478   0.3064   1.0000
  11.250   1.6781   0.01145   0.00693  -0.0477   0.2993   1.0000
  11.500   1.7031   0.01187   0.00733  -0.0476   0.2910   1.0000
  11.750   1.7279   0.01228   0.00774  -0.0474   0.2813   1.0000
  12.000   1.7518   0.01280   0.00824  -0.0473   0.2700   1.0000
  12.250   1.7739   0.01348   0.00888  -0.0470   0.2563   1.0000
  12.500   1.7944   0.01432   0.00966  -0.0467   0.2414   1.0000
  12.750   1.8119   0.01540   0.01067  -0.0462   0.2247   1.0000
  13.000   1.8261   0.01670   0.01191  -0.0456   0.2076   1.0000
  13.250   1.8345   0.01839   0.01355  -0.0448   0.1890   1.0000
  13.500   1.8319   0.02087   0.01601  -0.0438   0.1735   1.0000
  13.750   1.7919   0.02835   0.02370  -0.0464   0.1709   1.0000
  14.000   1.7529   0.03517   0.03064  -0.0474   0.1674   1.0000
  14.250   1.7174   0.04137   0.03690  -0.0480   0.1622   1.0000
  14.500   1.6823   0.04747   0.04304  -0.0487   0.1564   1.0000
  14.750   1.6575   0.05257   0.04818  -0.0491   0.1498   1.0000
  15.000   1.6352   0.05765   0.05325  -0.0497   0.1416   1.0000
  15.250   1.6163   0.06251   0.05808  -0.0503   0.1326   1.0000
  15.500   1.6009   0.06708   0.06264  -0.0508   0.1241   1.0000
  15.750   1.5901   0.07113   0.06668  -0.0513   0.1162   1.0000
  16.000   1.5783   0.07541   0.07094  -0.0518   0.1083   1.0000
  16.250   1.5672   0.07968   0.07519  -0.0525   0.1014   1.0000
  16.500   1.5609   0.08338   0.07887  -0.0530   0.0943   1.0000
  16.750   1.5518   0.08760   0.08309  -0.0538   0.0883   1.0000
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