AAE251 HW 5
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Dec 6, 2023
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AAE 251: Introduction to Aerospace Design
Homework 5—Wind Tunnels, Lift, and Drag
Due Tuesday February 22
nd
, 11:59 PM ET on Gradescope
Instructions
Show all the work and clearly box your final answer. You will not receive full credit for
a correct final answer if you don’t show your work.
You must use the template provided. Anything that you want the graders to grade must
be written legibly within the boxes provided to you.
There are multiple steps involved to complete your submission on Gradescope. You can
follow the step-by-step guide posted on Brightspace.
Select the relevant pages of your
final answer for each question in your Gradescope submission.
2
Question 1 (5 points)
Consider a low-speed open-circuit subsonic wind tunnel with an inlet-to-throat area
ratio of 12. The tunnel is turned on, and the pressure difference between the inlet (the
settling chamber) and the test section is read as a height difference of
10cm
on a U-
tube mercury manometer. The density of air is
1.225kg/m
!
and that of liquid mercury
is
1.36 × 10
"
kg/m
!
. Calculate the velocity of the air in the test section.
Answer 1:
3
Question 2 (8 points)
You are testing a model wing of constant chord length in a low-speed subsonic wind
tunnel, spanning the test section. The wing has an NACA 2412 airfoil and a chord
length of 0.6 m. The parameters for the full scale and wind tunnel models are as
follows:
Parameters
Full Scale Model
Wind Tunnel Model
Mach number
0.25
0.25
Density
0.019 kg/m
3
0.034 kg/m
3
Temperature
216.65 K
68.6 K
Speed of sound
295 m/s
166 m/s
Drag
95.6 N
To be computed
Assume that we can relate dynamic viscosity to temperature as follows:
/
#$%& ()%%*+ ,-&*+
/
.)++ /01+* ,-&*+
= 1
2
#$%& ()%%*+ ,-&*+
2
.)++ /01+* ,-&*+
3
!
"
(a)
Compute the chord length of the wind tunnel model of the airfoil.
(4 points)
Answer 2a:
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