NACA 16009 (naca16009-il)
NACA 16009 - NACA 16009 airfoil
| Details | Dat file | Parser | |
|
(naca16009-il) NACA 16009 NACA 16009 airfoil Max thickness 9% at 50% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA 16009 1.00000 0.00090 0.99893 0.00111 0.99572 0.00176 0.99039 0.00283 0.98296 0.00431 0.97347 0.00618 0.96194 0.00839 0.94844 0.01089 0.93301 0.01359 0.91573 0.01644 0.89668 0.01938 0.87592 0.02237 0.85355 0.02534 0.82967 0.02825 0.80438 0.03103 0.77779 0.03364 0.75000 0.03603 0.72114 0.03817 0.69134 0.04003 0.66072 0.04159 0.62941 0.04286 0.59755 0.04382 0.56526 0.04449 0.53270 0.04488 0.50000 0.04500 0.46730 0.04488 0.43474 0.04453 0.40245 0.04396 0.37059 0.04317 0.33928 0.04218 0.30866 0.04100 0.27886 0.03965 0.25000 0.03814 0.22221 0.03648 0.19562 0.03467 0.17033 0.03274 0.14645 0.03070 0.12408 0.02855 0.10332 0.02632 0.08427 0.02401 0.06699 0.02158 0.05156 0.01908 0.03806 0.01649 0.02653 0.01375 0.01704 0.01098 0.00961 0.00814 0.00428 0.00534 0.00107 0.00267 0.00000 0.00000 0.00107 -0.00267 0.00428 -0.00534 0.00961 -0.00814 0.01704 -0.01098 0.02653 -0.01375 0.03806 -0.01649 0.05156 -0.01908 0.06699 -0.02158 0.08427 -0.02401 0.10332 -0.02632 0.12408 -0.02855 0.14645 -0.03070 0.17033 -0.03274 0.19562 -0.03467 0.22221 -0.03648 0.25000 -0.03814 0.27886 -0.03965 0.30866 -0.04100 0.33928 -0.04218 0.37059 -0.04317 0.40245 -0.04396 0.43474 -0.04453 0.46730 -0.04488 0.50000 -0.04500 0.53270 -0.04488 0.56526 -0.04449 0.59755 -0.04382 0.62941 -0.04286 0.66072 -0.04159 0.69134 -0.04003 0.72114 -0.03817 0.75000 -0.03603 0.77779 -0.03364 0.80438 -0.03103 0.82967 -0.02825 0.85355 -0.02534 0.87592 -0.02237 0.89668 -0.01938 0.91573 -0.01644 0.93301 -0.01359 0.94844 -0.01089 0.96194 -0.00839 0.97347 -0.00618 0.98296 -0.00431 0.99039 -0.00283 0.99572 -0.00176 0.99893 -0.00111 1.00000 -0.00090 |
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for NACA 16009 (naca16009-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca16009-il | 50,000 | 9 | 18 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16009-il | 50,000 | 5 | 19.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16009-il | 100,000 | 9 | 25.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16009-il | 100,000 | 5 | 28.8 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16009-il | 200,000 | 9 | 39.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16009-il | 200,000 | 5 | 34.6 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16009-il | 500,000 | 9 | 44.6 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16009-il | 500,000 | 5 | 38 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16009-il | 1,000,000 | 9 | 47 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16009-il | 1,000,000 | 5 | 47.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||