NN7 MK20 (nn7mk20-il)
NN7 MK20 - NN7 MK20 airfoil
| Details | Dat file | Parser | |
|
(nn7mk20-il) NN7 MK20 NN7 MK20 airfoil Max thickness 16.9% at 37.1% chord. Max camber 3% at 59.8% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NN7 MK20 1.00000 0.00000 0.99893 0.00029 0.99572 0.00115 0.99039 0.00258 0.98296 0.00456 0.97347 0.00704 0.96194 0.00994 0.94844 0.01323 0.93301 0.01691 0.91573 0.02105 0.89668 0.02573 0.87592 0.03093 0.85355 0.03654 0.82967 0.04241 0.80438 0.04851 0.77779 0.05490 0.75000 0.06159 0.72114 0.06846 0.69134 0.07531 0.66072 0.08198 0.62941 0.08834 0.59755 0.09426 0.56526 0.09960 0.53270 0.10420 0.50000 0.10792 0.46730 0.11068 0.43474 0.11249 0.40245 0.11342 0.37059 0.11346 0.33928 0.11260 0.30866 0.11080 0.27886 0.10810 0.25000 0.10456 0.22221 0.10033 0.19562 0.09549 0.17033 0.09012 0.14645 0.08422 0.12408 0.07784 0.10332 0.07102 0.08427 0.06385 0.06699 0.05642 0.05156 0.04890 0.03806 0.04133 0.02653 0.03369 0.01704 0.02605 0.00961 0.01834 0.00428 0.01100 0.00107 0.00487 0.00000 0.00000 0.00107 -0.00401 0.00428 -0.00792 0.00961 -0.01202 0.01704 -0.01595 0.02653 -0.01978 0.03806 -0.02366 0.05156 -0.02752 0.06699 -0.03122 0.08427 -0.03465 0.10332 -0.03790 0.12408 -0.04112 0.14645 -0.04428 0.17033 -0.04716 0.19562 -0.04957 0.22221 -0.05152 0.25000 -0.05310 0.27886 -0.05437 0.30866 -0.05521 0.33928 -0.05546 0.37059 -0.05511 0.40245 -0.05427 0.43474 -0.05291 0.46730 -0.05084 0.50000 -0.04786 0.53270 -0.04390 0.56526 -0.03908 0.59755 -0.03361 0.62941 -0.02771 0.66072 -0.02161 0.69134 -0.01558 0.72114 -0.00996 0.75000 -0.00515 0.77779 -0.00145 0.80438 0.00109 0.82967 0.00264 0.85355 0.00340 0.87592 0.00357 0.89668 0.00331 0.91573 0.00283 0.93301 0.00232 0.94844 0.00186 0.96194 0.00146 0.97347 0.00107 0.98296 0.00071 0.99039 0.00040 0.99572 0.00018 0.99893 0.00004 1.00000 0.00000 |
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for NN7 MK20 (nn7mk20-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| nn7mk20-il | 50,000 | 9 | 21 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nn7mk20-il | 50,000 | 5 | 17.2 at α=12° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nn7mk20-il | 100,000 | 9 | 44.2 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nn7mk20-il | 100,000 | 5 | 43.8 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nn7mk20-il | 200,000 | 9 | 70.2 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nn7mk20-il | 200,000 | 5 | 69.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nn7mk20-il | 500,000 | 9 | 101.8 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nn7mk20-il | 500,000 | 5 | 99 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nn7mk20-il | 1,000,000 | 9 | 127.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nn7mk20-il | 1,000,000 | 5 | 118.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||