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3 years ago

Check pics to help me out on a pennfoster exam. Will mark brainliest if I pass the test. Thanks a lot.

Engineering

1 answer:

skad [1K]3 years ago

8 0

6. Fuel, oxygen and an ignition source must be present to start a fire.

7. Flash arrester

8. The location where a drill bit enters a workpiece.

9. Paper, oxygen and an ignition source.

10. Boom supported aerial lifts.

Explanation:

6. Fuel, air and an ignition source are included in “Fire Triangle”. These three conditions represent an essential prerequisite for starting a fire.

7. Flash arrester is a safety device used in welding torches to stop the reverse flow of the flame thereby protecting the user from any further damage.

8. Point of Operation refers to the place at which work is being performed. In the case of drill bit working, the workplace is the point where the drill bit enters the workpiece.

9. Class A fires are fire coming of from common materials such as paper, plastic, trash etc.

10. Fall protection refers to the safety net for the workers working at height. In the case of Boom supported aerial lifts, workers work at certain heights. Hence, they are equipped with fall protection gears.

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Describe two characteristics that bridges and skyscrapers have in common.

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Answer:

skyscrapers and bridges both have structural builds accounting for the influence of wind and they both cost big money

Explanation:

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3 years ago

Plot the absorbance, A, versus the FeSCN2 concentration of the standard solutions (the values from your Pre-lab assignment). Fro

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Answer:

Explanation:

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3 years ago

Explain the function of both of the organelles pictured below.

just olya [345]

Answer:

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6 0

3 years ago

A light aircraft with a wing area of 200 ft^2 and a weight of 2000 lb has a lift coefficient of 0.39 and a drag coefficient of 0

Gnoma [55]

Answer: power required to maintain level flight=82.20hp

Explanation:

Given

Area = 200 ft^2

Weight = 2000 lb

Cl( Lift coefficient)= 0.39

Cd( Drag coefficient) = 0.06

The density ρ of air at standard atmospheric pressure = 2.38 X 10^-3 slugs/ft^3

For Equilibrium to be maintained during flight conditions, the lift force must be balanced by the weight of the aircraft such that

Lift force = Weight of aircraft

(1/2)ρAU²Cl= W

1/2X 2.38 X 10^-3 X 200 X U² X 0.39 = 2000

U²= 2000 X 2 / 2.38 X 10^-3 X 200 X 0.39

U= $\sqrt{21,547.08}$

Velocity, U= 146.7892ft/s

Drag force of the velocity can be deduced from the formulae

Cd= Drag force(D) /1/2 ρU²A

Drag force=1/2 ρU²ACd

D=1/2 x (2.38 X 10^-3 slugs/ft^3) x (146.7892ft/s)² x 200 ft^2 x 0.06

D=307.69

Drag force= 308lb

power required to maintain level flight is given as

P = Drag force x Velocity = D x U

=308lb X 146.7892ft/s

=45,211.0736lb.ft/s

Changing to hp we have that

1 Horsepower, hp = 550 ft lbf/s

??=45,211.0736lb.ft/s

45,211.0736lb.ft/s/ 550 ft lbf/s= 82.20hp

6 0

3 years ago

A flywheel made of Grade 30 cast iron (UTS = 217 MPa, UCS = 763 MPa, E = 100 GPa, density = 7100 Kg/m, Poisson's ratio = 0.26) h

hram777 [196]

Answer:

N = 38546.82 rpm

Explanation:

$D_{1}$ = 150 mm

$A_{1}= \frac{\pi }{4}\times 150^{2}$

= 17671.45 $mm^{2}$

$D_{2}$ = 250 mm

$A_{2}= \frac{\pi }{4}\times 250^{2}$

= 49087.78 $mm^{2}$

The centrifugal force acting on the flywheel is fiven by

F = M ( $R_{2}$ - $R_{1}$ ) x $w^{2}$ ------------(1)

Here F = ( -UTS x $A_{1}$ + UCS x $A_{2}$ )

Since density, $\rho = \frac{M}{V}$

$\rho = \frac{M}{A\times t}$

$M = \rho \times A\times t$ $M = 7100 \times \frac{\pi }{4}\left ( D_{2}^{2}-D_{1}^{2} \right )\times t$

$M = 7100 \times \frac{\pi }{4}\left ( 250^{2}-150^{2} \right )\times 37$

$M = 8252963901$

∴ $R_{2}$ - $R_{1}$ = 50 mm

∴ F = $763\times \frac{\pi }{4}\times 250^{2}-217\times \frac{\pi }{4}\times 150^{2}$

F = 33618968.38 N --------(2)

Now comparing (1) and (2)

$33618968.38 = 8252963901\times 50\times \omega ^{2}$

∴ ω = 4036.61

We know

$\omega = \frac{2\pi N}{60}$

$4036.61 = \frac{2\pi N}{60}$

∴ N = 38546.82 rpm

7 0

4 years ago