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tamaranim1 [39]
2 years ago
6

A particle of mass m moves in the xy plane with a velocity of v = vxî + vyĵ. Determine the angular momentum of the particle abou

t the origin when its position vector is r = xî + yĵ. (Use the following as necessary: x, y, vx, vy, and m.)
Physics
1 answer:
alexira [117]2 years ago
5 0

Answer:

L=m(xv_y-yv_x)k

Explanation:

It is given that,

Velocity of a particle, v=v_xi+v_yj

Position vector of a particle, r=xi+yj

We need to find the angular momentum of the particle. It is given by :

L=r\times p, p = linear momentum

L=r\times (mv)

L=m(r\times v)

L=m((xi+yj)\times (v_xi+v_yj))

L=m(xv_y-yv_x)k

So, the angular momentum of the particle is (xv_y-yv_x)k. Hence, this is the required solution.

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30) A force produces power P by doing work W in a time T. What power will be produced by a force that does six times as much wor
schepotkina [342]

Answer:

A) 12P

Explanation:

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At the beginning in this problem, we have:

W = work done by the force

T = time taken

So the power produced is

P=\frac{W}{T}

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W'=6W

And this work is done in half the time, so the new time is

T'=\frac{T}{2}

Substituting into the equation of the power, we find the new power produced:

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4 0
2 years ago
An airplane weighing 5000 lb is flying at standard sea level with a velocity of 200 mi/h. At this velocity the L/D ratio is a ma
saul85 [17]

Answer:

98.15 lb

Explanation:

weight of plane (W) = 5,000 lb

velocity (v) = 200 m/h =200 x 88/60 = 293.3 ft/s

wing area (A) = 200 ft^{2}

aspect ratio (AR) = 8.5

Oswald efficiency factor (E) = 0.93

density of air (ρ) = 1.225 kg/m^{3} = 0.002377 slugs/ft^{3}

Drag = 0.5 x ρ x v^{2} x A x Cd

we need to get the drag coefficient (Cd) before we can solve for the drag

Drag coefficient (Cd) = induced drag coefficient (Cdi) + drag coefficient at zero lift (Cdo)

where

  • induced drag coefficient (Cdi) = \frac{Cl^{2} }{n.E.AR} (take note that π is shown as n and ρ is shown as p)    

        where lift coefficient (Cl)= \frac{2W}{pAv^{2} }=\frac{2x5000}{0.002377x200x293.3^{2} } = 0.245

        therefore

       induced drag coefficient (Cdi) = \frac{Cl^{2} }{n.E.AR} = \frac{0.245^{2} }{3.14x0.93x8.5} = 0.0024

  • since the airplane flies at maximum L/D ratio, minimum lift is required and hence induced drag coefficient (Cdi) = drag coefficient at zero lift (Cdo)
  • Cd = 0.0024 + 0.0024 = 0.0048

Now that we have the coefficient of drag (Cd) we can substitute it into the formula for drag.        

 Drag = 0.5 x ρ x v^{2} x A x Cd

Drag = 0.5 x 0.002377 x (293.3 x 293.3) x 200 x 0.0048 = 98.15 lb

8 0
2 years ago
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