S4061-096-84 (s4061-il)
S4061-096-84 - Selig S4061 low Reynolds number airfoil
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(s4061-il) S4061-096-84 Selig S4061 low Reynolds number airfoil Max thickness 9.6% at 30.9% chord. Max camber 3.3% at 44.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
S4061-096-84 1.00000 0.0 0.99675 0.00034 0.98709 0.00147 0.97129 0.00363 0.94977 0.00698 0.92304 0.01156 0.89171 0.01729 0.85637 0.02403 0.81765 0.03151 0.77610 0.03945 0.73227 0.04752 0.68665 0.05541 0.63971 0.06283 0.59189 0.06949 0.54359 0.07519 0.49522 0.07974 0.44716 0.08301 0.39979 0.08491 0.35348 0.08542 0.30862 0.08453 0.26554 0.08227 0.22460 0.07876 0.18619 0.07414 0.15074 0.06848 0.11855 0.06186 0.08988 0.05437 0.06493 0.04616 0.04385 0.03741 0.02676 0.02838 0.01380 0.01937 0.00502 0.01069 0.00046 0.00283 0.00079 -0.00320 0.00681 -0.00787 0.01835 -0.01209 0.03499 -0.01545 0.05666 -0.01780 0.08329 -0.01907 0.11475 -0.01932 0.15086 -0.01864 0.19130 -0.01724 0.23566 -0.01527 0.28346 -0.01291 0.33414 -0.01034 0.38708 -0.00771 0.44161 -0.00516 0.49704 -0.00279 0.55267 -0.00069 0.60777 0.00107 0.66164 0.00245 0.71357 0.00342 0.76289 0.00400 0.80895 0.00419 0.85115 0.00405 0.88894 0.00363 0.92184 0.00301 0.94940 0.00225 0.97127 0.00146 0.98714 0.00074 0.99678 0.00020 1.00001 -0.00000 |
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Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
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Polars for S4061-096-84 (s4061-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s4061-il | 50,000 | 9 | 35.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4061-il | 50,000 | 5 | 39.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4061-il | 100,000 | 9 | 59.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4061-il | 100,000 | 5 | 60.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4061-il | 200,000 | 9 | 84.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4061-il | 200,000 | 5 | 81.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4061-il | 500,000 | 9 | 116.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4061-il | 500,000 | 5 | 105.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4061-il | 1,000,000 | 9 | 139.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4061-il | 1,000,000 | 5 | 121.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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