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LNV109A (lnv109a-il)

LNV109A - Douglas/Liebeck LNV109A high lift airfoil


Airfoil lnv109a-il
Details Dat file Parser  
(lnv109a-il) LNV109A
Douglas/Liebeck LNV109A high lift airfoil
Max thickness 13% at 23.5% chord.
Max camber 6% at 31.5% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
 LNV109A
 1.000000 0.000000
 0.993938 0.000543
 0.986151 0.001101
 0.976665 0.001787
 0.965515 0.002657
 0.952740 0.003737
 0.938385 0.005056
 0.922500 0.006639
 0.905141 0.008509
 0.886369 0.010690
 0.866250 0.013204
 0.844856 0.016069
 0.822261 0.019300
 0.798545 0.022912
 0.773791 0.026914
 0.748087 0.031312
 0.721524 0.036110
 0.694194 0.041303
 0.666193 0.046886
 0.637621 0.052846
 0.608579 0.059164
 0.579167 0.065813
 0.549490 0.072756
 0.519653 0.079934
 0.489759 0.087276
 0.459916 0.094701
 0.430226 0.102116
 0.400796 0.109249
 0.371729 0.115295
 0.343127 0.119496
 0.315090 0.121941
 0.287718 0.122784
 0.261106 0.122185
 0.235350 0.120264
 0.210538 0.117155
 0.186758 0.113001
 0.164095 0.107922
 0.142628 0.102024
 0.122432 0.095430
 0.103579 0.088284
 0.086135 0.080712
 0.070162 0.072825
 0.055715 0.064730
 0.042846 0.056528
 0.031599 0.048318
 0.022015 0.040194
 0.014127 0.032222
 0.007963 0.024369
 0.003544 0.016413
 0.000887 0.008081
 0.000000 0.000000
 0.000887 -.008081
 0.003544 -.015530
 0.007963 -.022138
 0.014127 -.027272
 0.022015 -.030455
 0.031599 -.031544
 0.042846 -.031202
 0.055715 -.030105
 0.070162 -.028554
 0.086135 -.026666
 0.103579 -.024529
 0.122432 -.022211
 0.142628 -.019767
 0.164095 -.017246
 0.186758 -.014689
 0.210538 -.012132
 0.235350 -.009608
 0.261106 -.007151
 0.287718 -.004782
 0.315090 -.002532
 0.343127 -.000425
 0.371729 0.001516
 0.400796 0.003265
 0.430226 0.004793
 0.459916 0.006064
 0.489759 0.006997
 0.519653 0.007552
 0.549490 0.007802
 0.579167 0.007826
 0.608579 0.007672
 0.637621 0.007376
 0.666193 0.006968
 0.694194 0.006477
 0.721524 0.005927
 0.748087 0.005340
 0.773791 0.004735
 0.798545 0.004130
 0.822261 0.003538
 0.844856 0.002973
 0.866250 0.002443
 0.886369 0.001955
 0.905141 0.001515
 0.922500 0.001126
 0.938385 0.000789
 0.952740 0.000505
 0.965515 0.000273
 0.976665 0.000093
 0.986151 -.000038
 0.993938 -.000097
 1.000000 0.000000
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Polars for LNV109A (lnv109a-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   lnv109a-il50,00095.5 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   lnv109a-il50,00059.8 at α=2.25°Mach=0 Ncrit=5Xfoil predictionDetails
   lnv109a-il100,00097 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   lnv109a-il100,000523.3 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   lnv109a-il200,000925.5 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   lnv109a-il200,000558.3 at α=9.5°Mach=0 Ncrit=5Xfoil predictionDetails
   lnv109a-il500,0009111.2 at α=11.25°Mach=0 Ncrit=9Xfoil predictionDetails
   lnv109a-il500,0005113.7 at α=10°Mach=0 Ncrit=5Xfoil predictionDetails
   lnv109a-il1,000,0009151.5 at α=10°Mach=0 Ncrit=9Xfoil predictionDetails
   lnv109a-il1,000,0005149.6 at α=9°Mach=0 Ncrit=5Xfoil predictionDetails
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