LIEBECK LA5055 AIRFOIL (la5055-il)
LIEBECK LA5055 AIRFOIL - Liebeck high lift airfoil
| Details | Dat file | Parser | |
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(la5055-il) LIEBECK LA5055 AIRFOIL Liebeck high lift airfoil Max thickness 15.9% at 35% chord. Max camber 5.9% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
LIEBECK LA5055 AIRFOIL
25. 25.
0.000000 0.000000
0.012500 0.030600
0.025000 0.042600
0.037500 0.052800
0.050000 0.061100
0.075000 0.076900
0.100000 0.088000
0.150000 0.106500
0.200000 0.118500
0.250000 0.128700
0.300000 0.134300
0.350000 0.138900
0.400000 0.137000
0.450000 0.131500
0.500000 0.119400
0.550000 0.103700
0.600000 0.087000
0.650000 0.070400
0.700000 0.058300
0.750000 0.045400
0.800000 0.032400
0.850000 0.022200
0.900000 0.014800
0.950000 0.006500
1.000000 0.000000
0.000000 0.000000
0.012500 -0.025900
0.025000 -0.031500
0.037500 -0.032400
0.050000 -0.032400
0.075000 -0.031500
0.100000 -0.030600
0.150000 -0.028700
0.200000 -0.027800
0.250000 -0.025000
0.300000 -0.023100
0.350000 -0.020400
0.400000 -0.018500
0.450000 -0.014800
0.500000 -0.013900
0.550000 -0.012000
0.600000 -0.010200
0.650000 -0.008300
0.700000 -0.007400
0.750000 -0.005600
0.800000 -0.003700
0.850000 -0.001900
0.900000 -0.000900
0.950000 -0.000500
1.000000 0.000000
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Polars for LIEBECK LA5055 AIRFOIL (la5055-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| la5055-il | 50,000 | 9 | 4.9 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la5055-il | 50,000 | 5 | 8.7 at α=13.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la5055-il | 100,000 | 9 | 18.7 at α=15.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la5055-il | 100,000 | 5 | 15.5 at α=13.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la5055-il | 200,000 | 9 | 24.7 at α=13.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la5055-il | 200,000 | 5 | 46.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la5055-il | 500,000 | 9 | 116.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la5055-il | 500,000 | 5 | 104.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la5055-il | 1,000,000 | 9 | 149.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la5055-il | 1,000,000 | 5 | 83.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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