S4158 (s4158-il)
S4158 - Selig S4158 low Reynolds number airfoil
| Details | Dat file | Parser | |
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(s4158-il) S4158 Selig S4158 low Reynolds number airfoil Max thickness 10.9% at 35.3% chord. Max camber 3.7% at 44.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
S4158 1.00000 0.00000 0.99654 0.00023 0.98621 0.00111 0.96923 0.00307 0.94604 0.00654 0.91742 0.01182 0.88428 0.01890 0.84751 0.02757 0.80801 0.03745 0.76666 0.04799 0.72424 0.05830 0.68083 0.06722 0.63593 0.07442 0.58958 0.08025 0.54234 0.08482 0.49464 0.08805 0.44690 0.08996 0.39957 0.09057 0.35312 0.08992 0.30808 0.08804 0.26485 0.08486 0.22375 0.08044 0.18512 0.07496 0.14936 0.06857 0.11693 0.06137 0.08808 0.05342 0.06297 0.04484 0.04177 0.03594 0.02474 0.02697 0.01209 0.01814 0.00392 0.00965 0.00018 0.00185 0.00000 0.00000 0.00127 -0.00429 0.00801 -0.00894 0.02053 -0.01294 0.03845 -0.01613 0.06167 -0.01849 0.09001 -0.02012 0.12317 -0.02113 0.16075 -0.02160 0.20228 -0.02159 0.24730 -0.02109 0.29534 -0.02016 0.34590 -0.01888 0.39838 -0.01735 0.45218 -0.01565 0.50667 -0.01385 0.56120 -0.01202 0.61511 -0.01022 0.66775 -0.00852 0.71848 -0.00696 0.76666 -0.00556 0.81168 -0.00437 0.85297 -0.00337 0.88999 -0.00257 0.92225 -0.00193 0.94931 -0.00140 0.97083 -0.00087 0.98668 -0.00035 0.99659 -0.00005 1.00000 0.00000 |
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Polars for S4158 (s4158-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s4158-il | 50,000 | 9 | 35.1 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4158-il | 50,000 | 5 | 32.7 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4158-il | 100,000 | 9 | 57.1 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4158-il | 100,000 | 5 | 55.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4158-il | 200,000 | 9 | 84.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4158-il | 200,000 | 5 | 80.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4158-il | 500,000 | 9 | 124.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4158-il | 500,000 | 5 | 109 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4158-il | 1,000,000 | 9 | 150.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4158-il | 1,000,000 | 5 | 124.3 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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