2.23 Hydrofoils & Propellers
Homework Assignment #3
Assigned:
Friday March. 2, 2007
Due: Monday March 9, 2007
1)
A system of straight line vortex segments is used to represent a swept wing as
shown below. All vortices have the same strength
Γ
, with directions as shown.
Γ
θ
∞
Y= 0
S/2
Y= s/4 ss/4s/4
S/2
Y= s/4
∞
Using your vortex segment function written in the last homework write a matlab
code to find the total induced velocity at the three points shown above as a function
of wing angle
θ
. Set
Γ
= 1 and
S=1 and vary
θ
from 10 degrees to 60 degrees. Plot
the induced velocity at these three points as a function of
θ
for these three points.
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View Full Document2) A planar foil is to be designed with spanwise circulation distribution as follows:
Γ
( ˜
y
)
=
2
Us
(
a
1
sin( ˜
y
)
+
a
3
sin(3˜
y
)
with a1 = 0.05 and a3 varies from 0.02 to 0.02
The span of the foil is 1 meter , the freestream speed U= 8m/s and the density of
the water is 998 kg/m3. The aspect ratio is 3:1.
a)
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 Spring '07
 PaulD.Sclavounos
 Aerodynamics, Lift, Airfoil, total drag, Total induced drag, total induced velocity

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