International Edition---engineering Mechanics: Statics, 4th Edition
4th Edition
ISBN: 9781305501607
Author: Andrew Pytel And Jaan Kiusalaas
Publisher: CENGAGE L
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Chapter 9, Problem 9.37P
The product of inertia of triangle (a) with respect to its centroid is
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Fy = 100 N
Fx = 100 N
Z
a = 500 mm
F₂ = 500 N
b = 1000 mm
Figure 2: Schematics for problem 3.
1. Draw the moment (M), axial (N), and shear (S) diagrams. Please note that this is a 3D problem and you
will have moment (M) and shear (S) along two different axes. That means that you will have a total of 5
diagrams.
I tried solving this one but have no idea where I went wrong can you please help me out with this?
Question 1.
A tube rotates in the horizontal xy plane with a constant angular velocity w about the z-axis. A
particle of mass m is released from a radial distance R when the tube is in the position shown.
This problem is based on problem 3.2 in the text.
y
ω
R
m
2R
Figure 1
X
a) Draw a free body diagram of the particle if the tube is frictionless.
b) Draw a free body diagram of the particle if the coefficient of friction between the sides of the
tube and the particle is μs = flk = fl.
c) For the case where the tube is frictionless, what is the radial speed at which the particle
leaves the tube?
d) For the case where there is friction, derive a differential equation that would allow you to
solve for the radius of the particle as a function of time. I'm only looking for the differential
equation. DO NOT solve it.
e) If there is no friction, what is the angle of the tube when the particle exits?
• Hint: You may need to solve a differential equation for the last part. The "potentially…
Chapter 9 Solutions
International Edition---engineering Mechanics: Statics, 4th Edition
Ch. 9 - Compute the moment of inertia of the shaded region...Ch. 9 - The properties of the plane region are...Ch. 9 - The moments of inertia of the plane region about...Ch. 9 - The moment of inertia of the plane region about...Ch. 9 - Using integration, find the moment of inertia and...Ch. 9 - Use integration to determine the moment of inertia...Ch. 9 - Determine Ix and Iy for the plane region using...Ch. 9 - Using integration, compute the polar moment of...Ch. 9 - Use integration to compute Ix and Iy for the...Ch. 9 - By integration, determine the moments of inertia...
Ch. 9 - Compute the moment of inertia about the x-axis for...Ch. 9 - By integration, find the moment of inertia about...Ch. 9 - Figure (a) shows the cross section of a column...Ch. 9 - Compute the dimensions of the rectangle shown in...Ch. 9 - Compute Ix and Iy for the W867 shape dimensioned...Ch. 9 - Figure (a) shows the cross-sectional dimensions...Ch. 9 - A W867 section is joined to a C1020 section to...Ch. 9 - Compute Ix and Iy for the region shown.Ch. 9 - Prob. 9.19PCh. 9 - Calculate Ix for the shaded region, knowing that...Ch. 9 - Compute Iy for the region shown, given that...Ch. 9 - Prob. 9.22PCh. 9 - Prob. 9.23PCh. 9 - Determine Ix for the triangular region shown.Ch. 9 - Determine the distance h for which the moment of...Ch. 9 - A circular region of radius R/2 is cut out from...Ch. 9 - Prob. 9.27PCh. 9 - Determine the ratio a/b for which Ix=Iy for the...Ch. 9 - As a round log passes through a sawmill, two slabs...Ch. 9 - Prob. 9.30PCh. 9 - By numerical integration, compute the moments of...Ch. 9 - Use numerical integration to compute the moments...Ch. 9 - The plane region A is submerged in a fluid of...Ch. 9 - Use integration to verify the formula given in...Ch. 9 - For the quarter circle in Table 9.2, verify the...Ch. 9 - Determine the product of inertia with respect to...Ch. 9 - The product of inertia of triangle (a) with...Ch. 9 - Prob. 9.38PCh. 9 - For the region shown, Ixy=320103mm4 and Iuv=0....Ch. 9 - Prob. 9.40PCh. 9 - Calculate the product of inertia with respect to...Ch. 9 - Prob. 9.42PCh. 9 - Prob. 9.43PCh. 9 - The figure shows the cross section of a standard...Ch. 9 - Prob. 9.45PCh. 9 - Prob. 9.46PCh. 9 - Prob. 9.47PCh. 9 - Use numerical integration to compute the product...Ch. 9 - Determine the dimension b of the square cutout so...Ch. 9 - For the rectangular region, determine (a) the...Ch. 9 - Prob. 9.51PCh. 9 - Prob. 9.52PCh. 9 - Prob. 9.53PCh. 9 - Prob. 9.54PCh. 9 - Prob. 9.55PCh. 9 - The u- and v-axes are the principal axes of the...Ch. 9 - The x- and y-axes are the principal axes for the...Ch. 9 - Prob. 9.58PCh. 9 - The inertial properties of the region shown with...Ch. 9 - Determine Iu for the inverted T-section shown....Ch. 9 - Using Ix and Iu from Table 9.2, determine the...Ch. 9 - Show that every axis passing through the centroid...Ch. 9 - Prob. 9.63PCh. 9 - The L806010-mm structural angle has the following...Ch. 9 - Compute the principal centroidal moments of...Ch. 9 - Prob. 9.66PCh. 9 - Determine the principal axes and the principal...Ch. 9 - Compute the principal centroidal moments of...Ch. 9 - Find the moments and the product of inertia of the...Ch. 9 - Determine the moments and product of inertia of...Ch. 9 - Find the principal moments of inertia and the...Ch. 9 - Determine the moments and product of inertia of...Ch. 9 - Prob. 9.73PCh. 9 - Prob. 9.74PCh. 9 - The u- and v-axes are the principal axes of the...Ch. 9 - The x- and y-axes are the principal axes for the...Ch. 9 - Prob. 9.77PCh. 9 - The L806010-mm structural angle has the following...Ch. 9 - Prob. 9.79RPCh. 9 - Prob. 9.80RPCh. 9 - By integration, show that the product of inertia...Ch. 9 - Compute Ix and Iy for the shaded region.Ch. 9 - Using integration, evaluate the moments of inertia...Ch. 9 - The inertial properties at point 0 for a plane...Ch. 9 - Compute Ix and Iy for the shaded region.Ch. 9 - The flanged bolt coupling is fabricated by...Ch. 9 - Prob. 9.87RPCh. 9 - Compute Ix,Iy, and Ixy for the shaded region.Ch. 9 - Determine Ix and Ixy for the shaded region shown.Ch. 9 - Calculate Ix,Iy, and Ixy for the shaded region...Ch. 9 - For the shaded region shown, determine (a) Ix and...Ch. 9 - Use integration to find Ix,Iy, and Ixy for the...Ch. 9 - Determine the principal moments of inertia and the...Ch. 9 - The properties of the unequal angle section are...
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- I tried this problem but I can't seem to figure out what I am missing here can you please help me?arrow_forwardSolve 4.9 row a USING THE ANALYTICAL METHODarrow_forwardcutting Instructions: Do not copy the drawing. Draw In third-angle orthographic projection, and to scale 1:1, the following views of the hinge: A sectional front view on A-A A top view ⚫ A right view (Show all hidden detail) Show the cutting plane in the top view . Label the sectioned view Note: All views must comply with the SABS 0111 Code of Practice for Engineering Drawing. Galaxy A05s Assessment criteria: ⚫ Sectional front view 026 12 042 66 [30] 11 10arrow_forward
- 1. Plot the moment (M), axial (N), and shear (S) diagrams as functions of z. a) b) F₁ = 1250 N F₁ = 600 N M₁ = 350 000 N mm F2 = 500 N 200 N a = 600 mm b=1000 mm a=750 mm b = 1000 mm d) M₁ = 350 000 N mm F₁ = 600 N F₂ =200 N a = 600 mm b = 1000 mm M₁ 175 000 Nmm F = 900 N a-250 mm b-1000 mm -250 mm. Figure 1: Schematics problem 1.arrow_forwardGiven the following cross-sections (with units in mm): b) t=2 b=25 h=25 t = 1.5 b=20 b=25 t=2 I t = 1.5 a=10 b=15 h-25 b=15 t=3 T h=25 Figure 3: Cross-sections for problem 2. 1. For each of them, calculate the position of the centroid of area with respect to the given coordinate system and report them in the table below. 2. For each of them, calculate the second moments of inertia I... and I, around their respective centroid of area and report them in the table below. Note: use the parallel axes theorem as much as possible to minimize the need to solve integrals. Centroid position x y box Moment of inertia lyy by a) b) c) d) e)arrow_forwardProblem 1: Analyze the canard-wing combination shown in Fig. 1. The canard and wing are made of the same airfoil section and have AR AR, S = 0.25, and = 0.45% 1. Develop an expression for the moment coefficient about the center of gravity in terms of the shown parameters (, and zg) and the three-dimensional aerodynamic characteristics of the used wing/canard (CL C and CM). 2. What is the range of the cg location for this configuration to be statically stable? You may simplify the problem by neglecting the upwash (downwash) effects between the lifting surfaces and the drag contribution to the moment. You may also assume small angle approximation. Figure 1: Canard-Wing Configuration.arrow_forward
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