Consider an infinitely thin flat plate with a 1 m chord at an angle of attack of 10◦ in a supersonic flow. The pressure and shear stress distributions on the upper and lower surfaces are given by pu = 4 × 104(x − 1)2 + 5.4 × 104, pl = 2 × 104(x − 1)2 + 1.73 × 105, τu = 288x−0.2, and τl = 731x−0.2, respectively, where x is the distance from the leading edge in meters and p and τ are in newtons per square meter. Calculate the normal and axial forces, the lift and drag, moments about the leading edge, and moments about the quarter chord, all per unit span. Also, calculate the location of the center of pressure.

Consider an infinitely thin flat plate with a 1 m chord at an angle of attack of 10◦ in a supersonic flow. The pressure and shear stress distributions on the upper and lower surfaces are given by pu = 4 × 104(x − 1)2 + 5.4 × 104, pl = 2 × 104(x − 1)2 + 1.73 × 105, τu = 288x−0.2, and τl = 731x−0.2, respectively, where x is the distance from the leading edge in meters and p and τ are in newtons per square meter. Calculate the normal and axial forces, the lift and drag, moments about the leading edge, and moments about the quarter chord, all per unit span. Also, calculate the location of the center of pressure.

Name: Consider an infinitely thin flat plate with a 1 m chord at an angle of
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Description: Consider an infinitely thin flat plate with a 1 m chord at an angle of attackof 10◦ in a supersonic flow. The pressure and shear stress distributions onthe upper and lower surfaces are given by pu = 4 × 104(x − 1)2 +5.4 × 104, pl = 2 × 104(x − 1)2 +

Calculus For The Life Sciences

2nd Edition

ISBN:9780321964038

Author:GREENWELL, Raymond N., RITCHEY, Nathan P., Lial, Margaret L.

Publisher:GREENWELL, Raymond N., RITCHEY, Nathan P., Lial, Margaret L.

Chapter3: The Derivative

Section3.3: Rates Of Change

Problem 29E: Explain the difference between the average rate of change of y as x changes a to b, and the...

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