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How do you read a 4 digit NACA airfoil?
The NACA four-digit wing sections define the profile by:
- First digit describing maximum camber as percentage of the chord.
- Second digit describing the distance of maximum camber from the airfoil leading edge in tenths of the chord.
- Last two digits describing maximum thickness of the airfoil as percent of the chord.
How do you calculate airfoil coordinates?
In this case, multiply the chord of the airfoil you are plotting times percent of the station/ordinate pairs in percent. In other words, if the number given is 1.25 then multiply times 1.25%. If your calculator does not have a percent key, then multiply times 1.25 and then divide by 100.
How do I find my NACA number?
NACA 4 digit airfoil specification
- M is the maximum camber divided by 100. In the example M=2 so the camber is 0.02 or 2% of the chord.
- P is the position of the maximum camber divided by 10. In the example P=4 so the maximum camber is at 0.4 or 40% of the chord.
- XX is the thickness divided by 100.
What does the first digit of 5 series NACA represents?
In a NACA 5-digit series (NACA 23012), the first digit (2) means the approximate camber in the percentage of chord, the second digit (3) indicates twice the position of the maximum camber in tenths of a chord, the third digit is either 0 or 1 and distinguishes the type of mean camber line, and the last two digits (12) …
Is NACA 2412 symmetrical?
For example, the NACA 2412 airfoil has a maximum camber of 2% located 40% (0.4 chords) from the leading edge with a maximum thickness of 12% of the chord. The NACA 0015 airfoil is symmetrical, the 00 indicating that it has no camber.
Is the first digit of a NACA airfoil symmetrical?
The airfoil is symmetrical if chord line and mean camber line coincide. The first digit shows the magnitude of maximum camber as the percentage of chord length. For NACA 2412 airfoil, the maximum camber is 2% of the chord length.
What does the second digit in NACA 2412 mean?
The second digit indicates the position of maximum camber from the airfoil leading edge in tenths of the chord. For NACA 2412 airfoil, the maximum camber is located at 40% of the chord length from the leading edge. The last two digits give the maximum thickness of the airfoil as the percentage of the chord length.
Where do you find the coordinates of an airfoil?
where x = coordinates along the length of the airfoil, from 0 to c (which stands for chord, or length) y = coordinates above and below the line extending along the length of the airfoil, these are either y. t for thickness coordinates or y.
What is the maximum camber of a NACA 4412 airfoil?
•The NACA 4412 airfoil section is a 12% thick airfoil which has a 4% maximum camber located at 4/10ths (40%) of the chord. 10 NACA FOUR-DIGIT SERIES