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LNV109A (lnv109a-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: LNV109A (lnv109a-il)
Reynolds number: 500,000
Max Cl/Cd: 113.73 at α=10°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-lnv109a-il-500000-n5.txt
Download as CSV file: xf-lnv109a-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.2255   0.08968   0.08515   0.0009   0.4304   0.0272
  -7.000  -0.2200   0.08682   0.08229  -0.0004   0.4298   0.0275
  -6.750  -0.2155   0.08393   0.07941  -0.0017   0.4292   0.0275
  -6.500  -0.2127   0.08111   0.07661  -0.0029   0.4285   0.0275
  -6.250  -0.2117   0.07841   0.07392  -0.0041   0.4278   0.0277
  -6.000  -0.2047   0.07522   0.07073  -0.0068   0.4270   0.0277
  -5.750  -0.1958   0.07170   0.06720  -0.0102   0.4264   0.0279
  -5.500  -0.1933   0.06254   0.05798  -0.0210   0.4263   0.0288
  -5.250  -0.1739   0.06054   0.05597  -0.0229   0.4257   0.0290
  -4.750  -0.1373   0.02668   0.02086  -0.0522   0.4255   0.0324
  -4.500  -0.1109   0.02475   0.01872  -0.0529   0.4247   0.0327
  -4.250  -0.0838   0.02337   0.01718  -0.0532   0.4238   0.0329
  -4.000  -0.0565   0.02205   0.01568  -0.0535   0.4229   0.0333
  -3.750  -0.0292   0.02055   0.01395  -0.0537   0.4219   0.0337
  -3.500  -0.0017   0.01914   0.01228  -0.0537   0.4210   0.0343
  -3.250   0.0260   0.01787   0.01073  -0.0537   0.4201   0.0349
  -3.000   0.0542   0.01685   0.00944  -0.0536   0.4191   0.0357
  -2.750   0.0826   0.01614   0.00851  -0.0534   0.4182   0.0362
  -2.500   0.1110   0.01569   0.00801  -0.0533   0.4171   0.0366
  -2.250   0.1396   0.01536   0.00764  -0.0531   0.4160   0.0369
  -2.000   0.1683   0.01507   0.00730  -0.0529   0.4149   0.0373
  -1.750   0.1970   0.01477   0.00694  -0.0527   0.4138   0.0377
  -1.500   0.2257   0.01448   0.00659  -0.0525   0.4129   0.0382
  -1.250   0.2545   0.01420   0.00623  -0.0522   0.4120   0.0387
  -1.000   0.2832   0.01394   0.00590  -0.0520   0.4110   0.0393
  -0.750   0.3120   0.01376   0.00563  -0.0518   0.4098   0.0399
  -0.500   0.3407   0.01358   0.00541  -0.0516   0.4087   0.0405
  -0.250   0.3695   0.01338   0.00524  -0.0514   0.4078   0.0411
   0.000   0.3983   0.01322   0.00510  -0.0512   0.4068   0.0417
   0.250   0.4272   0.01307   0.00497  -0.0510   0.4058   0.0424
   0.500   0.4560   0.01294   0.00484  -0.0508   0.4048   0.0431
   0.750   0.4849   0.01281   0.00472  -0.0507   0.4037   0.0439
   1.000   0.5138   0.01270   0.00460  -0.0505   0.4024   0.0446
   1.250   0.5425   0.01256   0.00449  -0.0503   0.4011   0.0455
   1.500   0.5714   0.01248   0.00443  -0.0501   0.3998   0.0466
   1.750   0.6002   0.01241   0.00438  -0.0500   0.3986   0.0480
   2.000   0.6290   0.01236   0.00433  -0.0498   0.3976   0.0493
   2.250   0.6578   0.01228   0.00427  -0.0496   0.3965   0.0506
   2.500   0.6865   0.01224   0.00425  -0.0495   0.3954   0.0522
   2.750   0.7153   0.01222   0.00422  -0.0493   0.3942   0.0542
   3.000   0.7439   0.01223   0.00424  -0.0492   0.3928   0.0565
   3.250   0.7726   0.01223   0.00429  -0.0490   0.3917   0.0599
   3.500   0.8014   0.01223   0.00435  -0.0489   0.3906   0.0639
   3.750   0.8301   0.01224   0.00442  -0.0488   0.3892   0.0693
   4.000   0.8587   0.01224   0.00449  -0.0487   0.3877   0.0786
   4.250   0.8873   0.01222   0.00456  -0.0486   0.3861   0.0995
   4.500   0.9157   0.01215   0.00466  -0.0485   0.3845   0.1532
   4.750   0.9436   0.01193   0.00480  -0.0484   0.3831   0.3065
   5.250   1.0052   0.01073   0.00499  -0.0494   0.3802   1.0000
   5.500   1.0336   0.01082   0.00504  -0.0493   0.3787   1.0000
   5.750   1.0618   0.01095   0.00513  -0.0491   0.3773   1.0000
   6.000   1.0901   0.01108   0.00529  -0.0490   0.3756   1.0000
   6.250   1.1184   0.01121   0.00545  -0.0489   0.3737   1.0000
   6.500   1.1466   0.01134   0.00559  -0.0488   0.3717   1.0000
   6.750   1.1748   0.01145   0.00572  -0.0487   0.3696   1.0000
   7.000   1.2029   0.01155   0.00583  -0.0486   0.3676   1.0000
   7.250   1.2310   0.01166   0.00593  -0.0485   0.3657   1.0000
   7.500   1.2589   0.01177   0.00602  -0.0484   0.3638   1.0000
   7.750   1.2867   0.01192   0.00619  -0.0483   0.3618   1.0000
   8.000   1.3145   0.01209   0.00642  -0.0482   0.3594   1.0000
   8.250   1.3421   0.01225   0.00662  -0.0482   0.3568   1.0000
   8.500   1.3697   0.01240   0.00679  -0.0481   0.3542   1.0000
   8.750   1.3972   0.01254   0.00695  -0.0480   0.3517   1.0000
   9.000   1.4245   0.01270   0.00709  -0.0479   0.3492   1.0000
   9.250   1.4516   0.01290   0.00735  -0.0478   0.3465   1.0000
   9.500   1.4787   0.01310   0.00762  -0.0477   0.3429   1.0000
   9.750   1.5055   0.01326   0.00777  -0.0476   0.3369   1.0000
  10.000   1.5319   0.01347   0.00798  -0.0475   0.3269   1.0000
  10.250   1.5573   0.01377   0.00826  -0.0474   0.3156   1.0000
  10.500   1.5821   0.01417   0.00862  -0.0473   0.3060   1.0000
  10.750   1.6071   0.01456   0.00903  -0.0471   0.2970   1.0000
  11.000   1.6309   0.01506   0.00953  -0.0469   0.2879   1.0000
  11.250   1.6533   0.01568   0.01013  -0.0467   0.2775   1.0000
  11.500   1.6747   0.01639   0.01083  -0.0464   0.2656   1.0000
  11.750   1.6941   0.01726   0.01169  -0.0461   0.2529   1.0000
  12.000   1.7099   0.01843   0.01284  -0.0457   0.2387   1.0000
  12.250   1.7210   0.01995   0.01434  -0.0452   0.2245   1.0000
  12.500   1.7224   0.02224   0.01665  -0.0447   0.2109   1.0000
  12.750   1.6945   0.02807   0.02265  -0.0465   0.2056   1.0000
  13.000   1.6586   0.03440   0.02906  -0.0473   0.1994   1.0000
  13.250   1.6272   0.04003   0.03474  -0.0476   0.1938   1.0000
  13.500   1.5997   0.04525   0.03999  -0.0480   0.1864   1.0000
  13.750   1.5767   0.05008   0.04483  -0.0483   0.1790   1.0000
  14.000   1.5562   0.05483   0.04959  -0.0488   0.1711   1.0000
  14.250   1.5400   0.05942   0.05416  -0.0494   0.1613   1.0000
  14.500   1.5263   0.06384   0.05856  -0.0501   0.1518   1.0000
  14.750   1.5136   0.06827   0.06297  -0.0508   0.1430   1.0000
  15.000   1.5031   0.07252   0.06720  -0.0515   0.1340   1.0000
  15.250   1.4950   0.07656   0.07122  -0.0522   0.1252   1.0000
  15.500   1.4864   0.08075   0.07540  -0.0531   0.1173   1.0000
  15.750   1.4788   0.08487   0.07950  -0.0539   0.1092   1.0000
  16.000   1.4723   0.08895   0.08357  -0.0548   0.1022   1.0000
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