LISSAMAN 7769 AIRFOIL (l7769-il)
LISSAMAN 7769 AIRFOIL - Lissaman 7769 human powered aircraft airfoil
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(l7769-il) LISSAMAN 7769 AIRFOIL Lissaman 7769 human powered aircraft airfoil Max thickness 11% at 30% chord. Max camber 4.4% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
LISSAMAN 7769 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0225000
0.0250000 0.0334000
0.0500000 0.0496000
0.0750000 0.0615000
0.1000000 0.0706000
0.1500000 0.0840000
0.2000000 0.0926000
0.3000000 0.0992000
0.4000000 0.0897000
0.5000000 0.0696000
0.6000000 0.0486000
0.7000000 0.0316000
0.8000000 0.0181000
0.9000000 0.0084000
0.9500000 0.0041000
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0164000
0.0250000 -.0201000
0.0500000 -.0230000
0.0750000 -.0230000
0.1000000 -.0216000
0.1500000 -.0170000
0.2000000 -.0138000
0.3000000 -.0106000
0.4000000 -.0091000
0.5000000 -.0075000
0.6000000 -.0060000
0.7000000 -.0045000
0.8000000 -.0030000
0.9000000 -.0016000
0.9500000 -.0008000
1.0000000 0.0000000
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Polars for LISSAMAN 7769 AIRFOIL (l7769-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| l7769-il | 50,000 | 9 | 6.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l7769-il | 50,000 | 5 | 15.4 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l7769-il | 100,000 | 9 | 32.3 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l7769-il | 100,000 | 5 | 39.8 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l7769-il | 200,000 | 9 | 72.6 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l7769-il | 200,000 | 5 | 74.3 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l7769-il | 500,000 | 9 | 113.7 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l7769-il | 500,000 | 5 | 111 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l7769-il | 1,000,000 | 9 | 143.8 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l7769-il | 1,000,000 | 5 | 136.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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