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LNV109A (lnv109a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: LNV109A (lnv109a-il)
Reynolds number: 1,000,000
Max Cl/Cd: 149.57 at α=9°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-lnv109a-il-1000000-n5.txt
Download as CSV file: xf-lnv109a-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3364   0.11718   0.11336   0.0140   0.4235   0.0197
 -10.000  -0.3265   0.11467   0.11085   0.0127   0.4230   0.0198
  -8.000  -0.5068   0.02265   0.01762  -0.0570   0.4232   0.0279
  -7.750  -0.4836   0.02011   0.01473  -0.0575   0.4226   0.0282
  -7.500  -0.4578   0.01883   0.01323  -0.0576   0.4218   0.0284
  -7.250  -0.4310   0.01793   0.01217  -0.0574   0.4209   0.0286
  -7.000  -0.4036   0.01724   0.01135  -0.0572   0.4199   0.0288
  -6.750  -0.3767   0.01638   0.01036  -0.0571   0.4190   0.0290
  -6.500  -0.3489   0.01585   0.00975  -0.0569   0.4182   0.0292
  -6.250  -0.3209   0.01543   0.00927  -0.0566   0.4174   0.0294
  -6.000  -0.2927   0.01507   0.00885  -0.0563   0.4165   0.0296
  -5.750  -0.2643   0.01473   0.00846  -0.0561   0.4157   0.0298
  -5.500  -0.2359   0.01441   0.00807  -0.0558   0.4148   0.0300
  -5.250  -0.2075   0.01409   0.00769  -0.0556   0.4139   0.0302
  -5.000  -0.1790   0.01377   0.00731  -0.0553   0.4129   0.0304
  -4.750  -0.1505   0.01346   0.00692  -0.0550   0.4117   0.0307
  -4.500  -0.1219   0.01316   0.00656  -0.0548   0.4103   0.0310
  -4.250  -0.0934   0.01289   0.00621  -0.0545   0.4090   0.0312
  -4.000  -0.0647   0.01259   0.00586  -0.0543   0.4086   0.0315
  -3.750  -0.0359   0.01232   0.00553  -0.0540   0.4081   0.0318
  -3.500  -0.0071   0.01206   0.00522  -0.0538   0.4076   0.0320
  -3.250   0.0219   0.01186   0.00497  -0.0535   0.4070   0.0323
  -3.000   0.0507   0.01160   0.00468  -0.0533   0.4063   0.0326
  -2.750   0.0796   0.01135   0.00442  -0.0530   0.4055   0.0329
  -2.500   0.1085   0.01117   0.00423  -0.0528   0.4045   0.0332
  -2.250   0.1375   0.01101   0.00406  -0.0526   0.4036   0.0335
  -2.000   0.1666   0.01087   0.00390  -0.0524   0.4027   0.0338
  -1.750   0.1956   0.01072   0.00375  -0.0521   0.4018   0.0342
  -1.500   0.2247   0.01059   0.00359  -0.0519   0.4009   0.0346
  -1.250   0.2538   0.01045   0.00344  -0.0517   0.3999   0.0350
  -1.000   0.2828   0.01032   0.00329  -0.0515   0.3988   0.0354
  -0.750   0.3119   0.01021   0.00315  -0.0513   0.3976   0.0358
  -0.500   0.3410   0.01011   0.00304  -0.0511   0.3966   0.0361
  -0.250   0.3700   0.00999   0.00291  -0.0509   0.3955   0.0367
   0.000   0.3990   0.00992   0.00284  -0.0507   0.3944   0.0373
   0.250   0.4280   0.00987   0.00279  -0.0505   0.3929   0.0378
   0.500   0.4571   0.00980   0.00273  -0.0503   0.3921   0.0383
   0.750   0.4863   0.00973   0.00267  -0.0502   0.3913   0.0389
   1.000   0.5154   0.00966   0.00262  -0.0500   0.3904   0.0396
   1.250   0.5445   0.00961   0.00257  -0.0498   0.3895   0.0402
   1.500   0.5736   0.00954   0.00252  -0.0497   0.3885   0.0409
   1.750   0.6027   0.00949   0.00250  -0.0495   0.3874   0.0418
   2.000   0.6318   0.00945   0.00248  -0.0494   0.3861   0.0428
   2.250   0.6609   0.00942   0.00246  -0.0493   0.3847   0.0441
   2.500   0.6900   0.00939   0.00245  -0.0491   0.3833   0.0453
   2.750   0.7190   0.00937   0.00244  -0.0490   0.3821   0.0469
   3.000   0.7480   0.00936   0.00244  -0.0489   0.3807   0.0486
   3.250   0.7769   0.00936   0.00245  -0.0488   0.3792   0.0505
   3.500   0.8058   0.00937   0.00248  -0.0487   0.3775   0.0531
   3.750   0.8348   0.00937   0.00252  -0.0486   0.3764   0.0564
   4.000   0.8637   0.00937   0.00257  -0.0485   0.3753   0.0615
   4.250   0.8926   0.00937   0.00262  -0.0484   0.3739   0.0696
   4.500   0.9215   0.00936   0.00268  -0.0483   0.3722   0.0834
   4.750   0.9503   0.00934   0.00274  -0.0482   0.3704   0.1123
   5.000   0.9789   0.00927   0.00283  -0.0481   0.3687   0.1789
   5.250   1.0071   0.00912   0.00294  -0.0481   0.3668   0.3100
   5.750   1.0676   0.00800   0.00321  -0.0490   0.3627   1.0000
   6.000   1.0963   0.00808   0.00330  -0.0490   0.3612   1.0000
   6.250   1.1249   0.00817   0.00340  -0.0489   0.3593   1.0000
   6.500   1.1534   0.00826   0.00350  -0.0488   0.3571   1.0000
   6.750   1.1819   0.00837   0.00359  -0.0487   0.3547   1.0000
   7.000   1.2102   0.00848   0.00369  -0.0486   0.3522   1.0000
   7.250   1.2384   0.00861   0.00381  -0.0486   0.3496   1.0000
   7.500   1.2667   0.00873   0.00394  -0.0485   0.3474   1.0000
   7.750   1.2949   0.00885   0.00407  -0.0485   0.3452   1.0000
   8.000   1.3231   0.00897   0.00421  -0.0484   0.3425   1.0000
   8.250   1.3511   0.00911   0.00435  -0.0484   0.3394   1.0000
   8.500   1.3789   0.00927   0.00451  -0.0483   0.3362   1.0000
   8.750   1.4067   0.00944   0.00468  -0.0482   0.3331   1.0000
   9.000   1.4344   0.00959   0.00485  -0.0482   0.3273   1.0000
   9.250   1.4612   0.00988   0.00508  -0.0481   0.3155   1.0000
   9.500   1.4872   0.01028   0.00541  -0.0481   0.2997   1.0000
   9.750   1.5131   0.01068   0.00576  -0.0480   0.2876   1.0000
  10.000   1.5387   0.01112   0.00616  -0.0479   0.2762   1.0000
  10.250   1.5637   0.01162   0.00661  -0.0478   0.2641   1.0000
  10.500   1.5882   0.01217   0.00711  -0.0476   0.2511   1.0000
  10.750   1.6116   0.01283   0.00772  -0.0475   0.2369   1.0000
  11.000   1.6337   0.01361   0.00844  -0.0473   0.2209   1.0000
  11.250   1.6542   0.01454   0.00929  -0.0470   0.2034   1.0000
  11.500   1.6727   0.01562   0.01029  -0.0466   0.1862   1.0000
  11.750   1.6881   0.01693   0.01153  -0.0462   0.1691   1.0000
  12.000   1.6996   0.01850   0.01304  -0.0456   0.1519   1.0000
  12.250   1.7017   0.02084   0.01534  -0.0451   0.1356   1.0000
  12.500   1.6765   0.02730   0.02200  -0.0482   0.1314   1.0000
  12.750   1.6406   0.03381   0.02863  -0.0491   0.1282   1.0000
  13.000   1.6137   0.03921   0.03411  -0.0497   0.1251   1.0000
  13.250   1.5895   0.04430   0.03925  -0.0503   0.1215   1.0000
  13.500   1.5676   0.04911   0.04410  -0.0507   0.1155   1.0000
  13.750   1.5512   0.05342   0.04842  -0.0511   0.1098   1.0000
  14.000   1.5364   0.05780   0.05281  -0.0516   0.1029   1.0000
  14.250   1.5299   0.06130   0.05631  -0.0519   0.0975   1.0000
  14.750   1.5156   0.06862   0.06363  -0.0526   0.0863   1.0000
  15.000   1.5113   0.07196   0.06696  -0.0528   0.0813   1.0000
  15.250   1.5063   0.07550   0.07052  -0.0533   0.0766   1.0000
  15.500   1.5029   0.07884   0.07387  -0.0536   0.0723   1.0000
  15.750   1.5007   0.08207   0.07709  -0.0540   0.0679   1.0000
  16.000   1.4970   0.08559   0.08063  -0.0545   0.0641   1.0000
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