A18 (original) (a18-il)
A18 (original) - Archer A18 F1C free flight airfoil(original)
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(a18-il) A18 (original) Archer A18 F1C free flight airfoil(original) Max thickness 7.3% at 30% chord. Max camber 3.9% at 45% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
A18 (original) 1.00000 0.00614 0.95000 0.01817 0.90000 0.02858 0.80000 0.04624 0.70000 0.06056 0.60000 0.07197 0.55000 0.07612 0.50000 0.07975 0.45000 0.08293 0.40000 0.08376 0.35000 0.08466 0.30000 0.08383 0.25000 0.08065 0.20000 0.07601 0.15000 0.07026 0.10000 0.06234 0.07500 0.05660 0.05000 0.04923 0.02500 0.03947 0.01250 0.03239 0.00000 0.01865 0.01250 0.00781 0.02500 0.00357 0.05000 0.00075 0.07500 0.00000 0.10000 0.00006 0.15000 0.00200 0.20000 0.00475 0.25000 0.00806 0.30000 0.01038 0.35000 0.01353 0.40000 0.01657 0.45000 0.01780 0.50000 0.01884 0.55000 0.01980 0.60000 0.01998 0.70000 0.01924 0.80000 0.01452 0.90000 0.00813 0.95000 0.00434 1.00000 0.00000 |
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Polars for A18 (original) (a18-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| a18-il | 50,000 | 9 | 44 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| a18-il | 50,000 | 5 | 44.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| a18-il | 100,000 | 9 | 65 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| a18-il | 100,000 | 5 | 63.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| a18-il | 200,000 | 9 | 86.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| a18-il | 200,000 | 5 | 80.7 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| a18-il | 500,000 | 9 | 111.9 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| a18-il | 500,000 | 5 | 99.6 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| a18-il | 1,000,000 | 9 | 124.7 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| a18-il | 1,000,000 | 5 | 109.6 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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