Consider the channel shown in (Figure 1). Suppose that a = 390 mm, b = 260 mm, c = 50 mm.

Need quick explanation, How to get 3m/s. [Do not copy]

A mechanic changing a tire rolls a wheel along the ground towards the car. The radius of the wheel is 42cm, and the speed of the wheel as it rolls is 2 revolutions per second. Height Above Ground (m) radiu HIDE wheel spet Time The diagram above illustrates the vertical motion of a point on the tire over time. It is possible to model the height of this point using a sinusoidal function of the form h(t)=-a sin[b(t-c)]+d. a) Determine the length of time required for one revolution of the tire. b) State the numerical value for each of the parameters a, b, c & d. And write a function representing the motion of the point in the form h(t)= -a sin[b(t−c)]+d.

how do I dimension the object shown below  assume grid spacing is 0.2

help please!!

sample calculations 目 File Edit View Insert Format Data To 100% $ % .0 .00 12: fx | A 1 Variable Value Units diameter height m 4 volume m^3 3 The image above shows a section of a Google sheet. What formula should be written in cell B4 to calculate the volume of a cylinder with a diameter value in B2 and height in B3? a) =0.25*PI()*B2^2 * B3 b) =PI()*B2^2 * B3 c) =pi*diameter^2 * height d) =PI*B2^2 * B3 3 5

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I need help with my MATLAB code. There is an error in the following code. The error says my orbitaldynamics function must return a column vector. Can you help me fix it? I tried changing the semi colon to a comma in dstate_dt = [v, a_total]; but it still gives me error   mu_earth = 398600.4418; % Earth's gravitational parameter (km^3/s^2) R_earth = 6378.137; % Earth's radius (km) C_d = 0.3; % Drag coefficient (assumed) A = 0.023; % Cross-sectional area of ISS (km^2) m = 420000; % Mass of ISS (kg)       % Initial conditions: position and velocity (ISS state vector) % ISS initial state vector (km and km/s) - sample data state_ISS =[-2.1195e+03, 3.9866e+03, 5.0692e+03, -5.3489, -5.1772, 1.8324];   % Time span for 10 revolutions T_orbit = 2 * pi * sqrt((norm(state_ISS(1:3))^3) / mu_earth); time_span = [0, 10 * T_orbit];     % Step 3: Numerical integration using ODE solver options = odeset('RelTol', 1e-12, 'AbsTol', 1e-12); [t, state] = ode45(@orbitalDynamics, time_span, state_ISS,…