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LNV109A (lnv109a-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: LNV109A (lnv109a-il)
Reynolds number: 500,000
Max Cl/Cd: 111.22 at α=11.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-lnv109a-il-500000.txt
Download as CSV file: xf-lnv109a-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2557   0.11086   0.10652   0.0101   0.4618   0.0350
  -8.500  -0.2590   0.10742   0.10310   0.0062   0.4614   0.0361
  -8.250  -0.2671   0.10402   0.09973   0.0019   0.4611   0.0362
  -8.000  -0.2505   0.10091   0.09662   0.0024   0.4602   0.0363
  -7.750  -0.2355   0.09825   0.09396   0.0025   0.4592   0.0365
  -7.500  -0.2238   0.09581   0.09153   0.0021   0.4583   0.0367
  -7.250  -0.2134   0.09345   0.08918   0.0014   0.4575   0.0369
  -7.000  -0.2040   0.09110   0.08684   0.0005   0.4566   0.0372
  -6.750  -0.1956   0.08870   0.08446  -0.0004   0.4556   0.0376
  -6.500  -0.1881   0.08629   0.08206  -0.0014   0.4546   0.0381
  -6.250  -0.1828   0.08381   0.07960  -0.0025   0.4537   0.0391
  -6.000  -0.1985   0.07832   0.07413  -0.0144   0.4537   0.0403
  -5.750  -0.1850   0.07574   0.07155  -0.0137   0.4527   0.0405
  -5.500  -0.1700   0.07354   0.06934  -0.0137   0.4517   0.0406
  -5.250  -0.1544   0.07142   0.06721  -0.0142   0.4508   0.0409
  -5.000  -0.1383   0.06915   0.06493  -0.0156   0.4498   0.0412
  -4.750  -0.1212   0.06677   0.06254  -0.0176   0.4488   0.0416
  -4.500  -0.1027   0.06420   0.05994  -0.0203   0.4478   0.0423
  -4.250  -0.0721   0.05611   0.05166  -0.0341   0.4470   0.0450
  -4.000  -0.0533   0.05465   0.05020  -0.0341   0.4453   0.0452
  -3.750  -0.0322   0.05288   0.04843  -0.0346   0.4446   0.0455
  -3.500  -0.0092   0.05088   0.04642  -0.0359   0.4438   0.0460
  -3.250   0.0328   0.04263   0.03777  -0.0459   0.4431   0.0498
  -3.000   0.0553   0.04120   0.03636  -0.0461   0.4421   0.0501
  -2.750   0.0794   0.03989   0.03505  -0.0464   0.4410   0.0504
  -2.500   0.1048   0.03851   0.03365  -0.0470   0.4399   0.0510
  -2.250   0.1407   0.03298   0.02763  -0.0509   0.4389   0.0555
  -2.000   0.1662   0.03203   0.02671  -0.0510   0.4377   0.0559
  -1.750   0.1925   0.03111   0.02578  -0.0512   0.4364   0.0566
  -1.500   0.2250   0.02776   0.02190  -0.0525   0.4352   0.0615
  -1.250   0.2517   0.02670   0.02086  -0.0526   0.4338   0.0621
  -1.000   0.2833   0.02172   0.01496  -0.0530   0.4329   0.0554
  -0.750   0.3114   0.02068   0.01389  -0.0529   0.4318   0.0542
  -0.500   0.3399   0.01934   0.01235  -0.0528   0.4307   0.0533
  -0.250   0.3687   0.01822   0.01098  -0.0526   0.4296   0.0526
   0.000   0.3974   0.01757   0.01014  -0.0524   0.4283   0.0527
   0.250   0.4256   0.01738   0.00984  -0.0522   0.4263   0.0532
   0.500   0.4547   0.01693   0.00931  -0.0520   0.4255   0.0541
   0.750   0.4837   0.01669   0.00898  -0.0517   0.4244   0.0550
   1.000   0.5122   0.01614   0.00845  -0.0516   0.4232   0.0557
   1.250   0.5408   0.01589   0.00824  -0.0514   0.4220   0.0567
   1.500   0.5694   0.01572   0.00810  -0.0512   0.4206   0.0578
   1.750   0.5981   0.01556   0.00795  -0.0510   0.4191   0.0591
   2.000   0.6267   0.01542   0.00780  -0.0508   0.4177   0.0605
   2.250   0.6552   0.01519   0.00760  -0.0506   0.4163   0.0624
   2.500   0.6837   0.01509   0.00753  -0.0504   0.4150   0.0646
   2.750   0.7124   0.01501   0.00745  -0.0502   0.4138   0.0668
   3.000   0.7408   0.01489   0.00735  -0.0500   0.4127   0.0695
   3.250   0.7694   0.01487   0.00733  -0.0498   0.4115   0.0733
   3.500   0.7976   0.01495   0.00742  -0.0496   0.4100   0.0786
   3.750   0.8255   0.01515   0.00768  -0.0495   0.4084   0.0863
   4.000   0.8540   0.01507   0.00772  -0.0494   0.4072   0.1031
   4.250   0.8811   0.01460   0.00794  -0.0493   0.4059   0.3554
   4.500   0.9146   0.01339   0.00808  -0.0505   0.4042   1.0000
   4.750   0.9430   0.01348   0.00815  -0.0503   0.4024   1.0000
   5.000   0.9714   0.01357   0.00822  -0.0502   0.4008   1.0000
   5.250   0.9997   0.01366   0.00829  -0.0500   0.3993   1.0000
   5.500   1.0282   0.01371   0.00830  -0.0498   0.3979   1.0000
   5.750   1.0567   0.01375   0.00829  -0.0496   0.3966   1.0000
   6.000   1.0851   0.01380   0.00829  -0.0495   0.3953   1.0000
   6.250   1.1133   0.01394   0.00838  -0.0493   0.3939   1.0000
   6.500   1.1409   0.01424   0.00868  -0.0492   0.3921   1.0000
   6.750   1.1687   0.01434   0.00884  -0.0491   0.3904   1.0000
   7.000   1.1965   0.01448   0.00903  -0.0490   0.3885   1.0000
   7.250   1.2243   0.01457   0.00916  -0.0489   0.3864   1.0000
   7.500   1.2523   0.01461   0.00922  -0.0487   0.3845   1.0000
   7.750   1.2805   0.01463   0.00923  -0.0486   0.3828   1.0000
   8.000   1.3087   0.01461   0.00920  -0.0485   0.3812   1.0000
   8.250   1.3370   0.01461   0.00917  -0.0483   0.3796   1.0000
   8.500   1.3648   0.01475   0.00927  -0.0482   0.3778   1.0000
   8.750   1.3917   0.01494   0.00955  -0.0481   0.3757   1.0000
   9.000   1.4187   0.01507   0.00977  -0.0480   0.3732   1.0000
   9.250   1.4461   0.01513   0.00988  -0.0479   0.3707   1.0000
   9.500   1.4740   0.01508   0.00985  -0.0478   0.3682   1.0000
   9.750   1.5025   0.01480   0.00953  -0.0476   0.3650   1.0000
  10.000   1.5300   0.01464   0.00940  -0.0475   0.3595   1.0000
  10.250   1.5576   0.01446   0.00926  -0.0474   0.3534   1.0000
  10.500   1.5847   0.01443   0.00917  -0.0472   0.3489   1.0000
  10.750   1.6109   0.01463   0.00948  -0.0471   0.3440   1.0000
  11.000   1.6371   0.01478   0.00968  -0.0470   0.3389   1.0000
  11.250   1.6628   0.01495   0.00982  -0.0468   0.3340   1.0000
  11.500   1.6882   0.01523   0.01021  -0.0467   0.3282   1.0000
  11.750   1.7129   0.01550   0.01049  -0.0465   0.3220   1.0000
  12.000   1.7372   0.01586   0.01091  -0.0463   0.3154   1.0000
  12.250   1.7602   0.01628   0.01134  -0.0460   0.3078   1.0000
  12.500   1.7827   0.01677   0.01189  -0.0458   0.2997   1.0000
  12.750   1.8028   0.01742   0.01253  -0.0454   0.2907   1.0000
  13.000   1.8210   0.01822   0.01335  -0.0449   0.2800   1.0000
  13.250   1.8360   0.01924   0.01439  -0.0443   0.2683   1.0000
  13.500   1.8441   0.02071   0.01589  -0.0435   0.2558   1.0000
  13.750   1.8332   0.02350   0.01874  -0.0424   0.2459   1.0000
  14.000   1.7931   0.03040   0.02576  -0.0442   0.2387   1.0000
  14.250   1.7602   0.03633   0.03175  -0.0449   0.2319   1.0000
  14.500   1.7240   0.04243   0.03787  -0.0454   0.2245   1.0000
  14.750   1.6957   0.04774   0.04320  -0.0458   0.2162   1.0000
  15.000   1.6675   0.05311   0.04857  -0.0463   0.2081   1.0000
  15.250   1.6464   0.05815   0.05360  -0.0470   0.1983   1.0000
  15.500   1.6283   0.06300   0.05844  -0.0478   0.1880   1.0000
  15.750   1.6117   0.06782   0.06322  -0.0487   0.1775   1.0000
  16.000   1.5942   0.07289   0.06826  -0.0497   0.1672   1.0000
  16.250   1.5790   0.07776   0.07309  -0.0507   0.1563   1.0000
  16.500   1.5642   0.08276   0.07806  -0.0518   0.1460   1.0000
  16.750   1.5523   0.08744   0.08270  -0.0529   0.1356   1.0000
  17.000   1.5396   0.09237   0.08760  -0.0542   0.1261   1.0000
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