Calculating the Ordinates to be Plotted
For this example I will be plotting a NACA 2412 airfoil. The
NACA 2412 is a semi-symmetrical airfoil (cambered) that is stable and
somewhat fast although it would not be the best choice for an extreme speed
aircraft. It would be a good choice for a one-design club racer
because it has no bad habits and will not get to speeds that the average
pilot can't handle.
The first table below is the set of ordinates for the NACA 2412. The
listing uses standard (1) above.
I will be calculating ordinates for and
plotting an airfoil having a 9" chord. Multiply all stations and ordinates
by the chord. Again, the numbers
given in the ordinate listing are percentages. That means you multiply
the chord by the station or ordinate
in percent.
To find the second station for example, multiply 9" x 1.25%.
The leading edge (L.E.) radius is also multiplied by the
chord to get the actual radius. This is also a percentage.
The second table contains the resulting numbers after multiplying
them by the wing
chord. All numbers are in inches for this example. Calculating
and plotting works the same regardless of your number system.
NACA 2412 Ordinates
|
Upper surface |
Lower surface |
Station |
Ordinate |
Station |
Ordinate |
0 |
0 |
0 |
0 |
1.25 |
2.15 |
1.25 |
1.65 |
2.5 |
2.99 |
2.5 |
- 2.27 |
5.0 |
4.13 |
5.0 |
- 3.01 |
7.5 |
4.96 |
7.5 |
- 3.46 |
10 |
5.63 |
10 |
- 3.75 |
15 |
6.61 |
15 |
- 4.10 |
20 |
7.26 |
20 |
- 4.23 |
25 |
7.67 |
25 |
- 4.22 |
30 |
7.88 |
30 |
- 4.12 |
40 |
7.80 |
40 |
- 3.80 |
50 |
7.24 |
50 |
- 3.34 |
60 |
6.36 |
60 |
- 2.76 |
70 |
5.18 |
70 |
- 2.14 |
80 |
3.75 |
80 |
- 1.50 |
90 |
2.08 |
90 |
- 0.82 |
95 |
1.14 |
95 |
- 0.48 |
100 |
0 |
100 |
0 |
L.E. radius: 1.58 |
Slope of radius through L.E.: 0.10 |
|
NACA 2412 (9" Chord)
|
Upper surface |
Lower surface |
Station |
Ordinate |
Station |
Ordinate |
0.000 |
0.000 |
0.000 |
0.000 |
0.113 |
0.194 |
0.113 |
-0.149 |
0.225 |
0.269 |
0.225 |
-0.204 |
0.450 |
0.372 |
0.450 |
-0.271 |
0.675 |
0.446 |
0.675 |
-0.311 |
0.900 |
0.507 |
0.900 |
-0.338 |
1.350 |
0.595 |
1.350 |
-0.369 |
1.800 |
0.653 |
1.800 |
-0.381 |
2.250 |
0.690 |
2.250 |
-0.380 |
2.700 |
0.709 |
2.700 |
-0.371 |
3.600 |
0.702 |
3.600 |
-0.342 |
4.500 |
0.652 |
4.500 |
-0.301 |
5.400 |
0.570 |
5.400 |
-0.248 |
6.300 |
0.466 |
6.300 |
-0.193 |
7.200 |
0.338 |
7.200 |
-0.135 |
8.100 |
0.187 |
8.100 |
-0.074 |
8.550 |
0.103 |
8.550 |
-0.043 |
9.000 |
0.000 |
9.000 |
0.000 |
L.E. Radius = 0.142 |
|
This particular airfoil has stations that
are identical for
both the upper and lower surfaces but that is not always true. Be sure to pay attention to what
you are doing. I have made the mistake of assuming the
stations were the same when they weren't which resulted in some strange
airfoil plots.
Now that you have the numbers they need to be plotted on paper. The ordinate/station
pairs are simply (x, y) coordinates. The Station is X and the Ordinate
is Y.
|