lab sheet

AE 341
AERODYNAMICS 1
2012-2013 FALL SEMESTER
LAB 5
In this lab experiment lift coefficient around NACA 0012 is aimed to be calculated at different
angles of attack. For this purpose NACA 0012 airfoil with 20 pressure tappings is placed in
AF100 subsonic wind tunnel. The airfoil has a span of 300mm and a chord length of 150mm.
Pressure measurements for different hole locations have been performed. In figure 1 airfoil
model with pressure tappings, pressure connections and assembly connection shaft are
shown. Locations of the pressure holes are shown in table 1.
Figure 1: Airfoil model, pressure connections and assembly model.

Table 1: Tapping positions on airfoil
Throughout the experiment pressure variation on the airfoil surfaces has been observed at
different angles of attack. A sample pressure variation is shown in figure 2. In the figure left
hand side measurements correspond to upper surface, while right hand side measurements
correspond to lower surface.
Figure 2: Sample pressure distribution over airfoil
For the laboratory report, prepare a chart including lab data and calculate the corresponding lift by
using the trapezoidal rule. Then, obtain the lift coefficient. A sample data table is shown in figure 3.

Figure 3: Blank result table

Notes:
Calculate the lift coefficient for different angles of attack, compare the results and comment
about the results.
There are 2 data sets in the course website. Please use the proper one according to your lab
group number. (Groups 1 to 8 will use the data for wind speed 20m/s case, groups 9 to 16 will
use the data for wind speed 27m/s case)
You can submit your lab reports until 7 th of January, 5pm. Late submissions will not be
accepted under any circumstances.
The students who will take lab make-up for previous experiments, contact with the course
assistant via e-mail and arrange a schedule.