LIEBECK L1003 AIRFOIL (l1003-il)
LIEBECK L1003 AIRFOIL - Liebeck high lift airfoil
| Details | Dat file | Parser | |
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(l1003-il) LIEBECK L1003 AIRFOIL Liebeck high lift airfoil Max thickness 17.7% at 30% chord. Max camber 6.5% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
LIEBECK L1003 AIRFOIL
25. 25.
0.000000 0.000000
0.012500 0.023070
0.025000 0.039810
0.037500 0.050930
0.050000 0.062960
0.075000 0.083330
0.100000 0.097220
0.150000 0.122220
0.200000 0.137040
0.250000 0.148150
0.300000 0.153700
0.350000 0.148150
0.400000 0.135180
0.450000 0.118520
0.500000 0.096300
0.550000 0.080560
0.600000 0.066670
0.650000 0.051850
0.700000 0.040740
0.750000 0.028700
0.800000 0.020370
0.850000 0.012040
0.900000 0.005560
0.950000 0.001850
1.000000 0.000000
0.000000 0.000000
0.012500 -0.037040
0.025000 -0.046300
0.037500 -0.049070
0.050000 -0.049070
0.075000 -0.043520
0.100000 -0.039810
0.150000 -0.033330
0.200000 -0.028700
0.250000 -0.025930
0.300000 -0.023150
0.350000 -0.020370
0.400000 -0.018520
0.450000 -0.016670
0.500000 -0.014810
0.550000 -0.012960
0.600000 -0.011110
0.650000 -0.009260
0.700000 -0.007410
0.750000 -0.005560
0.800000 -0.003700
0.850000 -0.002780
0.900000 -0.001850
0.950000 -0.000930
1.000000 0.000000
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Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
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Polars for LIEBECK L1003 AIRFOIL (l1003-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| l1003-il | 50,000 | 9 | 4.1 at α=14.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l1003-il | 50,000 | 5 | 5.2 at α=17.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l1003-il | 100,000 | 9 | 4.5 at α=14.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l1003-il | 100,000 | 5 | 7 at α=17.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l1003-il | 200,000 | 9 | 10.2 at α=18.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l1003-il | 200,000 | 5 | 10.1 at α=15.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l1003-il | 500,000 | 9 | 74.1 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l1003-il | 500,000 | 5 | 68.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l1003-il | 1,000,000 | 9 | 104.1 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l1003-il | 1,000,000 | 5 | 68.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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