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 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.
Physics for Scientists and Engineers: Foundations and Connections
1st Edition
ISBN:9781133939146
Author:Katz, Debora M.
Publisher:Katz, Debora M.
Chapter15: Fluids
Section: Chapter Questions
Problem 22PQ: A spherical submersible 2.00 m in radius, armed with multiple cameras, descends under water in a...
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I need help solving question number 1 please
![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](/v2/_next/image?url=https%3A%2F%2Fcontent.bartleby.com%2Fqna-images%2Fquestion%2Fc0e4ae0c-a85e-415a-9fa7-aab2307c195f%2Fdb859d95-f684-4aed-b43b-b5c5ba743b89%2Fq4bxw_processed.jpeg&w=3840&q=75)
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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