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LNV109A (lnv109a-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: LNV109A (lnv109a-il)
Reynolds number: 200,000
Max Cl/Cd: 58.31 at α=9.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-lnv109a-il-200000-n5.txt
Download as CSV file: xf-lnv109a-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2440   0.10822   0.10244   0.0073   0.4638   0.0445
  -8.000  -0.2430   0.10541   0.09965   0.0045   0.4631   0.0447
  -7.750  -0.2409   0.10254   0.09682   0.0021   0.4623   0.0448
  -7.500  -0.2274   0.09949   0.09379   0.0019   0.4611   0.0450
  -7.250  -0.2147   0.09680   0.09112   0.0016   0.4599   0.0452
  -7.000  -0.2039   0.09428   0.08861   0.0009   0.4588   0.0456
  -6.750  -0.1946   0.09182   0.08617   0.0000   0.4579   0.0460
  -6.500  -0.1864   0.08936   0.08374  -0.0011   0.4569   0.0466
  -6.250  -0.1794   0.08691   0.08132  -0.0022   0.4560   0.0473
  -6.000  -0.1752   0.08460   0.07904  -0.0033   0.4551   0.0479
  -5.750  -0.1717   0.08180   0.07624  -0.0070   0.4544   0.0492
  -5.500  -0.1651   0.07739   0.07180  -0.0162   0.4538   0.0497
  -5.250  -0.1502   0.07509   0.06952  -0.0151   0.4527   0.0500
  -5.000  -0.1345   0.07284   0.06727  -0.0154   0.4516   0.0504
  -4.750  -0.1182   0.07033   0.06474  -0.0172   0.4505   0.0509
  -4.500  -0.1006   0.06762   0.06200  -0.0198   0.4494   0.0515
  -4.000  -0.0545   0.05626   0.05033  -0.0340   0.4477   0.0450
  -3.750  -0.0309   0.05333   0.04729  -0.0364   0.4467   0.0445
  -3.500  -0.0021   0.04846   0.04220  -0.0415   0.4458   0.0447
  -3.250   0.0232   0.04593   0.03958  -0.0433   0.4449   0.0444
  -3.000   0.0506   0.04289   0.03643  -0.0456   0.4439   0.0442
  -2.750   0.0800   0.03916   0.03250  -0.0483   0.4428   0.0440
  -2.500   0.1126   0.03246   0.02515  -0.0520   0.4418   0.0446
  -2.250   0.1400   0.03109   0.02367  -0.0526   0.4403   0.0453
  -2.000   0.1678   0.02987   0.02234  -0.0530   0.4387   0.0459
  -1.750   0.1966   0.02770   0.01985  -0.0535   0.4372   0.0463
  -1.500   0.2252   0.02602   0.01786  -0.0538   0.4358   0.0468
  -1.250   0.2539   0.02463   0.01617  -0.0540   0.4345   0.0475
  -1.000   0.2828   0.02347   0.01467  -0.0540   0.4333   0.0487
  -0.750   0.3116   0.02254   0.01341  -0.0539   0.4322   0.0499
  -0.500   0.3398   0.02208   0.01290  -0.0537   0.4310   0.0506
  -0.250   0.3682   0.02163   0.01235  -0.0535   0.4298   0.0512
   0.000   0.3966   0.02121   0.01180  -0.0533   0.4286   0.0520
   0.250   0.4251   0.02084   0.01129  -0.0531   0.4275   0.0530
   0.500   0.4534   0.02057   0.01090  -0.0529   0.4263   0.0541
   0.750   0.4818   0.02038   0.01073  -0.0528   0.4249   0.0556
   1.000   0.5100   0.02030   0.01075  -0.0527   0.4233   0.0570
   1.250   0.5382   0.02021   0.01069  -0.0526   0.4215   0.0585
   1.500   0.5663   0.02008   0.01059  -0.0525   0.4197   0.0599
   1.750   0.5944   0.01997   0.01049  -0.0523   0.4179   0.0613
   2.000   0.6223   0.01989   0.01049  -0.0521   0.4163   0.0632
   2.250   0.6503   0.01988   0.01050  -0.0520   0.4150   0.0661
   2.500   0.6782   0.01983   0.01049  -0.0518   0.4137   0.0689
   2.750   0.7062   0.01980   0.01048  -0.0516   0.4125   0.0719
   3.000   0.7343   0.01975   0.01043  -0.0513   0.4114   0.0757
   3.250   0.7623   0.01973   0.01041  -0.0511   0.4103   0.0818
   3.500   0.7903   0.01973   0.01042  -0.0508   0.4092   0.0899
   3.750   0.8175   0.01997   0.01081  -0.0508   0.4074   0.1036
   4.000   0.8442   0.02022   0.01132  -0.0508   0.4051   0.1414
   4.250   0.8698   0.02004   0.01182  -0.0508   0.4029   0.3662
   4.750   0.9319   0.01938   0.01227  -0.0519   0.3990   1.0000
   5.000   0.9593   0.01960   0.01245  -0.0517   0.3975   1.0000
   5.250   0.9868   0.01979   0.01259  -0.0514   0.3962   1.0000
   5.500   1.0145   0.01992   0.01266  -0.0512   0.3950   1.0000
   5.750   1.0423   0.02001   0.01269  -0.0509   0.3939   1.0000
   6.000   1.0701   0.02012   0.01273  -0.0506   0.3928   1.0000
   6.250   1.0945   0.02093   0.01370  -0.0507   0.3898   1.0000
   6.500   1.1193   0.02159   0.01445  -0.0507   0.3868   1.0000
   6.750   1.1453   0.02196   0.01487  -0.0506   0.3844   1.0000
   7.000   1.1717   0.02221   0.01513  -0.0504   0.3826   1.0000
   7.250   1.1985   0.02236   0.01528  -0.0501   0.3810   1.0000
   7.500   1.2258   0.02241   0.01532  -0.0498   0.3797   1.0000
   7.750   1.2533   0.02241   0.01530  -0.0495   0.3785   1.0000
   8.000   1.2810   0.02242   0.01527  -0.0492   0.3774   1.0000
   8.250   1.2992   0.02390   0.01702  -0.0493   0.3725   1.0000
   8.500   1.3226   0.02445   0.01766  -0.0492   0.3697   1.0000
   8.750   1.3478   0.02469   0.01794  -0.0489   0.3675   1.0000
   9.000   1.3742   0.02472   0.01799  -0.0486   0.3658   1.0000
   9.250   1.4015   0.02464   0.01790  -0.0482   0.3644   1.0000
   9.500   1.4291   0.02451   0.01776  -0.0478   0.3631   1.0000
   9.750   1.4413   0.02631   0.01984  -0.0478   0.3579   1.0000
  10.000   1.4613   0.02700   0.02062  -0.0475   0.3546   1.0000
  10.250   1.4860   0.02708   0.02074  -0.0471   0.3523   1.0000
  10.500   1.5134   0.02683   0.02049  -0.0467   0.3503   1.0000
  10.750   1.5396   0.02665   0.02032  -0.0462   0.3475   1.0000
  11.000   1.5406   0.02894   0.02285  -0.0460   0.3400   1.0000
  11.250   1.5780   0.02738   0.02117  -0.0454   0.3352   1.0000
  11.500   1.4561   0.04239   0.03653  -0.0490   0.3227   1.0000
  11.750   1.4768   0.04251   0.03665  -0.0485   0.3179   1.0000
  12.250   1.3860   0.05798   0.05220  -0.0514   0.2965   1.0000
  12.500   1.4324   0.05502   0.04921  -0.0501   0.2938   1.0000
  12.750   1.3908   0.06263   0.05688  -0.0516   0.2834   1.0000
  13.000   1.4329   0.06006   0.05429  -0.0503   0.2798   1.0000
  13.250   1.4038   0.06637   0.06065  -0.0516   0.2703   1.0000
  13.500   1.4375   0.06477   0.05901  -0.0505   0.2655   1.0000
  13.750   1.4190   0.07006   0.06436  -0.0517   0.2565   1.0000
  14.000   1.4487   0.06890   0.06313  -0.0507   0.2507   1.0000
  14.250   1.4322   0.07414   0.06844  -0.0520   0.2415   1.0000
  14.500   1.4430   0.07559   0.06987  -0.0519   0.2339   1.0000
  14.750   1.4464   0.07811   0.07238  -0.0523   0.2251   1.0000
  15.000   1.4454   0.08132   0.07559  -0.0529   0.2164   1.0000
  15.250   1.4511   0.08354   0.07776  -0.0532   0.2072   1.0000
  15.500   1.4508   0.08667   0.08087  -0.0538   0.1973   1.0000
  15.750   1.4489   0.09011   0.08430  -0.0546   0.1874   1.0000
  16.000   1.4467   0.09363   0.08779  -0.0554   0.1772   1.0000
  16.250   1.4445   0.09719   0.09131  -0.0563   0.1669   1.0000
  16.500   1.4412   0.10093   0.09500  -0.0573   0.1567   1.0000
  16.750   1.4360   0.10510   0.09914  -0.0586   0.1468   1.0000
  17.000   1.4319   0.10912   0.10314  -0.0598   0.1371   1.0000
  17.250   1.4267   0.11337   0.10737  -0.0612   0.1282   1.0000
  17.500   1.4222   0.11756   0.11152  -0.0627   0.1198   1.0000
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