LNV109A (lnv109a-il)
LNV109A - Douglas/Liebeck LNV109A high lift airfoil
| Details | Dat file | Parser | |
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(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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Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
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Polars for LNV109A (lnv109a-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| lnv109a-il | 50,000 | 9 | 5.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lnv109a-il | 50,000 | 5 | 9.8 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lnv109a-il | 100,000 | 9 | 7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lnv109a-il | 100,000 | 5 | 23.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lnv109a-il | 200,000 | 9 | 25.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lnv109a-il | 200,000 | 5 | 58.3 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lnv109a-il | 500,000 | 9 | 111.2 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lnv109a-il | 500,000 | 5 | 113.7 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lnv109a-il | 1,000,000 | 9 | 151.5 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lnv109a-il | 1,000,000 | 5 | 149.6 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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