NACA-0009 9.0% smoothed (n0009sm-il)
NACA-0009 9.0% smoothed - NACA 0009 airfoil (smoothed)
| Details | Dat file | Parser | |
|
(n0009sm-il) NACA-0009 9.0% smoothed NACA 0009 airfoil (smoothed) Max thickness 9% at 30.9% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA-0009 9.0% smoothed 1.00000 0.0 0.99572 0.00057 0.98296 0.00218 0.96194 0.00463 0.93301 0.00770 0.89668 0.01127 0.85355 0.01522 0.80438 0.01945 0.75000 0.02384 0.69134 0.02823 0.62941 0.03247 0.56526 0.03638 0.50000 0.03978 0.43474 0.04248 0.37059 0.04431 0.33928 0.04484 0.30866 0.04509 0.27886 0.04504 0.25000 0.04466 0.22221 0.04397 0.19562 0.04295 0.17033 0.04161 0.14645 0.03994 0.12408 0.03795 0.10332 0.03564 0.08427 0.03305 0.06699 0.03023 0.05156 0.02720 0.03806 0.02395 0.02653 0.02039 0.01704 0.01646 0.00961 0.01214 0.00428 0.00767 0.00107 0.00349 0.0 0.0 0.00107 -0.00349 0.00428 -0.00767 0.00961 -0.01214 0.01704 -0.01646 0.02653 -0.02039 0.03806 -0.02395 0.05156 -0.02720 0.06699 -0.03023 0.08427 -0.03305 0.10332 -0.03564 0.12408 -0.03795 0.14645 -0.03994 0.17033 -0.04161 0.19562 -0.04295 0.22221 -0.04397 0.25000 -0.04466 0.27886 -0.04504 0.30866 -0.04509 0.33928 -0.04484 0.37059 -0.04431 0.43474 -0.04248 0.50000 -0.03978 0.56526 -0.03638 0.62941 -0.03247 0.69134 -0.02823 0.75000 -0.02384 0.80438 -0.01945 0.85355 -0.01522 0.89668 -0.01127 0.93301 -0.00770 0.96194 -0.00463 0.98296 -0.00218 0.99572 -0.00057 1.00000 0.0 |
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for NACA-0009 9.0% smoothed (n0009sm-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| n0009sm-il | 50,000 | 9 | 27 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n0009sm-il | 50,000 | 5 | 25.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n0009sm-il | 100,000 | 9 | 37.3 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n0009sm-il | 100,000 | 5 | 33.4 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n0009sm-il | 200,000 | 9 | 45.6 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n0009sm-il | 200,000 | 5 | 42.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n0009sm-il | 500,000 | 9 | 55.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n0009sm-il | 500,000 | 5 | 60.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n0009sm-il | 1,000,000 | 9 | 74.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n0009sm-il | 1,000,000 | 5 | 75.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||