S4110 (s4110-il)
S4110 - Selig S4110 low Reynolds number airfoil
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(s4110-il) S4110 Selig S4110 low Reynolds number airfoil Max thickness 8.4% at 26.6% chord. Max camber 3.1% at 45.4% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
S4110 1.00000 0.00000 0.99677 0.00055 0.98738 0.00228 0.97242 0.00521 0.95237 0.00908 0.92746 0.01359 0.89794 0.01868 0.86424 0.02430 0.82685 0.03033 0.78630 0.03657 0.74310 0.04282 0.69771 0.04883 0.65062 0.05439 0.60225 0.05934 0.55306 0.06352 0.50349 0.06683 0.45401 0.06922 0.40507 0.07062 0.35714 0.07102 0.31066 0.07042 0.26612 0.06885 0.22394 0.06631 0.18453 0.06285 0.14830 0.05849 0.11555 0.05328 0.08659 0.04729 0.06167 0.04060 0.04093 0.03323 0.02437 0.02536 0.01204 0.01730 0.00400 0.00935 0.00021 0.00191 0.00000 0.00000 0.00119 -0.00408 0.00755 -0.00892 0.01905 -0.01317 0.03554 -0.01630 0.05723 -0.01820 0.08413 -0.01911 0.11599 -0.01920 0.15247 -0.01865 0.19313 -0.01757 0.23751 -0.01605 0.28509 -0.01417 0.33537 -0.01202 0.38774 -0.00970 0.44162 -0.00728 0.49640 -0.00487 0.55145 -0.00258 0.60606 -0.00053 0.65957 0.00121 0.71127 0.00260 0.76051 0.00360 0.80665 0.00418 0.84906 0.00436 0.88717 0.00416 0.92046 0.00363 0.94843 0.00285 0.97068 0.00193 0.98686 0.00102 0.99670 0.00029 1.00000 0.00000 |
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Polars for S4110 (s4110-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s4110-il | 50,000 | 9 | 39.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4110-il | 50,000 | 5 | 40.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4110-il | 100,000 | 9 | 60.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4110-il | 100,000 | 5 | 57.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4110-il | 200,000 | 9 | 81.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4110-il | 200,000 | 5 | 73.5 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4110-il | 500,000 | 9 | 107.2 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4110-il | 500,000 | 5 | 89.9 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4110-il | 1,000,000 | 9 | 122.7 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4110-il | 1,000,000 | 5 | 99.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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