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Transcribed Image Text:Problem 1:
As shown in Fig. 1(a), a flat-plate airfoil with a chord length c has an angle of attack, a..
Surface pressures on the lower and upper surfaces are p1 and p2, respectively.
Calculate the lift and drag of the flat-plate airfoil.
Note: Decompose pressure vectors into the vertical and horizontal components that
contribute to the lift and drag, respectively.
Problem 2:
As shown in Fig. 1(b), a two-segment airfoil with a chord length c has a slope angle a..
Surface pressures on the two upper surfaces are p1 and p3, respectively. The pressure on
the lower surface is p2.
Calculate the lift and drag of the flat-plate airfoil.
Note: Decompose pressure vectors into the vertical and horizontal components that
contribute to the lift and drag, respectively. The chord length c is a distance between the
leading and trailing edges. You need to calculate the length of a segment.
a
(a)
pl
p2
p2
a
pl
(b)
p3
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