Consider an infinitely thin flat plate with a 5 m chord at an angle of attack of 5° in a supersonic flow. The pressure and shear stress distributions on the upper and lower surfaces are given by pu= 3 x 105 cos(TT x) + 4.9 x 105, pj= 6 x 105 cos(TT X) + 1.15 x 10°, Tu= 301x 0.4, and T/= 699x-0.4, respectively, where x is the distance from the leading edge in meters and p and 7 are in Newtons per square meter. Calculate the normal and axial forces, the lift and drag, moment about the leading edge, and moment about the one- quarter chord, all per unit span. Also, calculate the location of the center of pressure. (Round axial force to the nearest whole number and other answers to two decimal places.) Note: Do not use small-angle approximation. x 106 N/m. N/m. The normal force is The axial force is 106 105 N/m. The lift is N/m. The drag is
Consider an infinitely thin flat plate with a 5 m chord at an angle of attack of 5° in a supersonic flow. The pressure and shear stress distributions on the upper and lower surfaces are given by pu= 3 x 105 cos(TT x) + 4.9 x 105, pj= 6 x 105 cos(TT X) + 1.15 x 10°, Tu= 301x 0.4, and T/= 699x-0.4, respectively, where x is the distance from the leading edge in meters and p and 7 are in Newtons per square meter. Calculate the normal and axial forces, the lift and drag, moment about the leading edge, and moment about the one- quarter chord, all per unit span. Also, calculate the location of the center of pressure. (Round axial force to the nearest whole number and other answers to two decimal places.) Note: Do not use small-angle approximation. x 106 N/m. N/m. The normal force is The axial force is 106 105 N/m. The lift is N/m. The drag is
Chapter2: Loads On Structures
Section: Chapter Questions
Problem 1P
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![Consider an infinitely thin flat plate with a 5 m chord at an angle of attack of 5° in a supersonic flow. The pressure and shear stress
distributions on the upper and lower surfaces are given by pu= 3 x 105 cos(TT X) + 4.9 x
105, pj 6 x 105 cos(TT X) + 1.15 x
106, Tu=
301x
-0.4 and T/= 699x
-0.4
*, respectively, where x is the distance from the leading edge in meters and p and r are in Newtons per
square meter. Calculate the normal and axial forces, the lift and drag, moment about the leading edge, and moment about the one-
quarter chord, all per unit span. Also, calculate the location of the center of pressure. (Round axial force to the nearest whole number
and other answers to two decimal places.)
Note: Do not use small-angle approximation.
The normal force is
106 N/m.
The axial force is|
N/m.
The lift is
7x 106 N/m.
The drag is
x 105 N/m.
The moment about the leading edge is
106 N.
106
The moment about the one-quarter chord is
The location of the center of pressure is
N.
m.](/v2/_next/image?url=https%3A%2F%2Fcontent.bartleby.com%2Fqna-images%2Fquestion%2F4a6249e4-b819-4636-ae17-ad70411e65fc%2F2c183725-c4de-4c1f-95f9-2d8d52670baf%2F9421yno_processed.jpeg&w=3840&q=75)
Transcribed Image Text:Consider an infinitely thin flat plate with a 5 m chord at an angle of attack of 5° in a supersonic flow. The pressure and shear stress
distributions on the upper and lower surfaces are given by pu= 3 x 105 cos(TT X) + 4.9 x
105, pj 6 x 105 cos(TT X) + 1.15 x
106, Tu=
301x
-0.4 and T/= 699x
-0.4
*, respectively, where x is the distance from the leading edge in meters and p and r are in Newtons per
square meter. Calculate the normal and axial forces, the lift and drag, moment about the leading edge, and moment about the one-
quarter chord, all per unit span. Also, calculate the location of the center of pressure. (Round axial force to the nearest whole number
and other answers to two decimal places.)
Note: Do not use small-angle approximation.
The normal force is
106 N/m.
The axial force is|
N/m.
The lift is
7x 106 N/m.
The drag is
x 105 N/m.
The moment about the leading edge is
106 N.
106
The moment about the one-quarter chord is
The location of the center of pressure is
N.
m.
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