DU86-084/18 8.44% (du8608418-il)
DU86-084/18 8.44% - Deflt University DU 86-084/18 low Reynolds number airfoil
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(du8608418-il) DU86-084/18 8.44% Deflt University DU 86-084/18 low Reynolds number airfoil Max thickness 8.5% at 36.9% chord. Max camber 1% at 45.8% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
DU86-084/18 8.44% 1.00000 0.00000 0.99882 0.00014 0.99537 0.00058 0.98990 0.00119 0.98235 0.00178 0.97260 0.00240 0.96064 0.00315 0.94653 0.00408 0.93035 0.00530 0.91222 0.00684 0.89230 0.00877 0.87068 0.01098 0.84721 0.01342 0.82178 0.01677 0.79567 0.02203 0.77033 0.02796 0.74534 0.03265 0.71959 0.03627 0.69280 0.03929 0.66515 0.04192 0.63676 0.04423 0.60777 0.04626 0.57829 0.04801 0.54846 0.04950 0.51838 0.05075 0.48819 0.05175 0.45800 0.05250 0.42794 0.05301 0.39813 0.05328 0.36869 0.05329 0.33973 0.05306 0.31136 0.05257 0.28370 0.05183 0.25684 0.05085 0.23089 0.04962 0.20596 0.04815 0.18213 0.04645 0.15951 0.04452 0.13818 0.04235 0.11822 0.03995 0.09968 0.03730 0.08261 0.03442 0.06707 0.03133 0.05308 0.02804 0.04069 0.02459 0.02993 0.02100 0.02081 0.01729 0.01335 0.01353 0.00755 0.00971 0.00334 0.00595 0.00075 0.00252 0.00003 -.00047 0.00157 -.00310 0.00525 -.00577 0.01083 -.00852 0.01833 -.01117 0.02763 -.01377 0.03871 -.01624 0.05154 -.01857 0.06607 -.02073 0.08226 -.02270 0.10006 -.02447 0.11942 -.02604 0.14028 -.02740 0.16256 -.02855 0.18619 -.02950 0.21109 -.03024 0.23716 -.03080 0.26431 -.03117 0.29244 -.03138 0.32144 -.03144 0.35118 -.03136 0.38154 -.03115 0.41241 -.03082 0.44366 -.03038 0.47514 -.02986 0.50673 -.02926 0.53829 -.02860 0.56967 -.02786 0.60072 -.02706 0.63131 -.02620 0.66131 -.02526 0.69058 -.02422 0.71897 -.02309 0.74639 -.02181 0.77270 -.02039 0.79780 -.01873 0.82155 -.01672 0.84412 -.01415 0.86587 -.01104 0.88688 -.00800 0.90687 -.00539 0.92550 -.00332 0.94247 -.00179 0.95751 -.00081 0.97041 -.00029 0.98104 -.00002 0.98934 0.00004 0.99528 0.00003 0.99879 0.00001 1.00000 0.00000 |
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Polars for DU86-084/18 8.44% (du8608418-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| du8608418-il | 50,000 | 9 | 32.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du8608418-il | 50,000 | 5 | 31.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du8608418-il | 100,000 | 9 | 46.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du8608418-il | 100,000 | 5 | 43.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du8608418-il | 200,000 | 9 | 63.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du8608418-il | 200,000 | 5 | 53.8 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du8608418-il | 500,000 | 9 | 75.6 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du8608418-il | 500,000 | 5 | 59.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du8608418-il | 1,000,000 | 9 | 71 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du8608418-il | 1,000,000 | 5 | 70.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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