II) Using the aerodynamic data tables plot (by hand on a millimeter grid paper) the values of
following quantities versus the angle of attack :
a) Lift vs. angle of attack cl -
b) Lift with flap or slot vs. angle of attack cl* -
c) Drag vs. angle of attack cd -
d) Moment around the LE vs. angle of attack cm(LE) -
e) Location of the center of pressure vs. angle of attack xCP -
Note: plot the appropriate curves for all 3 airfoils in a single graph using different colors; for
example, all lift curves should be in the same graph for a direct comparison; another joint graph
for drag, etc. Use excel to calculate cm(LE) where needed, then plot graphs by hand.
Aerodynamic Data Table 1:
c
I
c
d
c
m(LE)
c *
I
(with slot)
-4
-0.14
0.014
-0.036
-0.27
-2
0.02
0.008
-0.052
-0.12
0
0.14
0.008
-0.09
0.03
2
0.32
0.012
-0.13
0.18
4
0.46
0.02
-0.16
0.33
6
0.6
0.03
-0.2
0.47
8
0.76
0.044
-0.24
0.62
10
0.9
0.06
-0.28
0.76
12
1.04
0.07
-0.31
0.9
14
1.16
0.096
-0.33
1.05
15
1.22
0.11
-0.34
1.12
16
1.16
0.14
-0.35
1.21
18
1.02
0.21
-0.384
1.36
20
0.94
0.26
-0.39
1.51
24
1.7
26
1.76
28
1.76
30
1.64
34
1.3
Aerodynamic Data Table 2:
c
I
c
d
c
m(AC)
c *
I
(with slot)
-8
-0.45
0.022
-0.097
0.9
-6
-0.23
0.014
-0.092
1.12
-4
-0.03
0.012
-0.092
1.34
-2
0.2
0.01
-0.092
1.56
0
0.38
0.01
-0.093
1.75
2
0.6
0.01
-0.095
1.95
4
0.8
0.012
-0.098
2.14
6
1
0.014
-0.1
2.43
8
1.15
0.017
-0.1
2.5
10
1.27
0.022
-0.095
2.65
12
1.36
0.03
-0.092
2.63
14
1.35
0.042
-0.092
16
1.25
0.059
-0.095
Aerodynamic Data Table 3:
c
I
c
d
c
m(c/4)
c *
I
(with slot)
-8
-0.68
0.02
-0.025
0.58
-6
-0.5
0.015
-0.026
0.8
-4
-0.33
0.013
-0.03
1.03
-2
-0.1
0.01
-0.033
1.25
0
0.12
0.009
-0.035
1.45
2
0.35
0.01
-0.037
1.63
4
0.55
0.011
-0.038
1.8
6
0.8
0.015
-0.039
1.87
8
0.95
0.023
-0.04
1.83
10
1.07
0.035
-0.04
1.7
12
1.06
0.05
-0.038
1.48
14
1.01
0.065
-0.035
c *
I
c c c
I d m(LE)
(with slot)
-4 -0.14 0.014 -0.036 -0.27
-2 0.02 0.008 -0.052 -0.12
0 0.14 0.008 -0.09 0.03
2 0.32 0.012 -0.13 0.18
4 0.46 0.02 -0.16 0.33
6 0.6 0.03 -0.2 0.47
8 0.76 0.044 -0.24 0.62
10 0.9 0.06 -0.28 0.76
12 1.04 0.07 -0.31 0.9
14 1.16 0.096 -0.33 1.05
15 1.22 0.11 -0.34 1.12
16 1.16 0.14 -0.35 1.21
18 1.02 0.21 -0.384 1.36
20 0.94 0.26 -0.39 1.51
24 1.7
26 1.76
28 1.76
30 1.64
34 1.3.
Mattingly "AI & Prompt Design: The Basics of Prompt Design"
II) Using the aerodynamic data tables plot (by hand on a millimeter gr.pdf
1. II) Using the aerodynamic data tables plot (by hand on a millimeter grid paper) the values of
following quantities versus the angle of attack :
a) Lift vs. angle of attack cl -
b) Lift with flap or slot vs. angle of attack cl* -
c) Drag vs. angle of attack cd -
d) Moment around the LE vs. angle of attack cm(LE) -
e) Location of the center of pressure vs. angle of attack xCP -
Note: plot the appropriate curves for all 3 airfoils in a single graph using different colors; for
example, all lift curves should be in the same graph for a direct comparison; another joint graph
for drag, etc. Use excel to calculate cm(LE) where needed, then plot graphs by hand.
Aerodynamic Data Table 1:
c I
c d
c m(LE)
c I
*
(with slot)
-4
-0.14
0.014
-0.036
-0.27
-2
0.02
0.008
-0.052
8. 0.059
-0.095
Aerodynamic Data Table 3:
c I
c d
c m(c/4)
c I
*
(with slot)
-8
-0.68
0.02
-0.025
0.58
-6
-0.5
0.015
-0.026
0.8
-4
-0.33
0.013
-0.03
1.03
