16.100 Homework Assignment # 4
Due: Monday, October 3 at 9am
Reading Assignment
Handout “Thin Airfoil Theory Summary”
Anderson, 3
rd
edition: Chapter 4 Section 4.1 – 4.9
Note: I did not give a targeted reading assignment for the problems, because essentially all of the
reading is useful for all of the problems.
Problem #1 (30%)
In this problem, we will consider the aerodynamic impact of leading and trailing edge flaps on an
airfoil using thin airfoil theory.
To be specific, we will consider the following camberline:
x
c
=
01
.
x
c
=
0 9
.
α
V
∞
η
0
η
1
where the leading and trailing edge flap deflection angles (defined positive downwards) are
η
0
and
η
1
, respectively.
In the following problems, use thin airfoil theory and assume small
angles throughout.
(a) Calculate the derivative of the lift coefficient with respect to the leading edge flap deflection,
∂
∂
c
l
/
η
0
.
(b) Calculate the derivative of the lift coefficient with respect to the trailing edge flap deflection,
∂
∂
c
l
/
η
1
.
(c) Show that trailing edge flap has a significantly greater impact on the lift coefficient than the
leading edge flap.
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 Fall '03
 willcox
 Dynamics, Aerodynamics, Airfoil, Wing design, Stall, airfoil theory, edge flap deflection, suction peak

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