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mestny [16]
3 years ago
13

From the information generated in Prob. 6.4 (from your previous Aero HW#1), calculate the maximum rate of climb for the single-e

ngine light plane at sea level and at 12,000-ft altitude.
Engineering
1 answer:
soldi70 [24.7K]3 years ago
5 0

Answer:

R/C @ sea Level = 42.5 ft/s

R/C @ 12,000 ft = 24.6 ft/s

Explanation:

Given:

- From problem in 6.4:

         excess power @ sea Level = 232 hp

         excess power @ 12,000 ft = 134 hp

- Thrust delivered by the engine P = 3000 lb

Find:

Maximum rate of climb R/C @ sea Level and @12,000 ft altitude.

Solution:

- Maximum rate of climb (i.e no drag + maximum lift) @ sea level:

                  R/C = excess [email protected] level / Thrust delivered by engine P

                  R/C = 232 hp*(550) / 3000 = 42.5 ft / s

- Maximum rate of climb (i.e no drag + maximum lift) @ 12,000 ft:

                  R/C = excess [email protected] level / Thrust delivered by engine P

                  R/C = 134 hp*(550) / 3000 = 24.6 ft / s              

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P9.28 A large vacuum tank, held at 60 kPa absolute, sucks sea- level standard air through a converging nozzle whose throat diame
eimsori [14]

Answer:

a)  m=0.17kg/s

b)  Ma=0.89

Explanation:

From the question we are told that:

Pressure P=60kPa

Diameter d=3cm

Generally at sea level

T_0=288k\\\\\rho_0=1.225kg/m^3\\\\P_0=101350Pa\\\\r=1.4

Generally the Power series equation for Mach number is mathematically given by

\frac{p_0}{p}=(1+\frac{r-1}{2}Ma^2)^{\frac{r}{r-1}}

\frac{101350}{60*10^3}=(1+\frac{1.4-1}{2}Ma^2)^{\frac{1.4}{1.4-1}}

Ma=0.89

Therefore

Mass flow rate

\frac{\rho_0}{\rho}=(1+\frac{1.4-1}{2}(0.89)^2)^{\frac{1.4}{1.4-1}}

\frac{1.225}{\rho}=(1+\frac{1.4-1}{2}(0.89)^2)^{\frac{1.4}{1.4-1}}

\rho=0.848kg/m^3

Generally the equation for Velocity at throat is mathematically given by

V=Ma(r*T_0\sqrt{T_e})

Where

T_e=\frac{P_e}{R\rho}\\\\T_e=\frac{60*10^6}{288*0.842\rho}

T_e=248

Therefore

V=0.89(1.4*288\sqrt{248})\\\\V=284

Generally the equation for Mass flow rate is mathematically given by

m=\rho*A*V

m=0.84*\frac{\pi}{4}*3*10^{-2}*284

m=0.17kg/s

6 0
2 years ago
Dampness or moisture introduces ____ into the weld, which causes cracking when some metals are welded.
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Answer: Dampness or moisture introduces hydrogen into the weld, which causes cracking when some metals are welded.

Explanation:

<em>This moisture (hydrogen) is a major cause of weld cracking and porosity. </em>

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Explanation:

Air fuel ratio:

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As we know that fuel burn in the presence of air that is why we have to maintain a proper amount of air fuel ratio.

When we need more power then we have supply more fuel and to burn this fuel ,require a specified amount of air.So for different loading condition of engine different air fuel ratio is required.

When air is less and fuel is more then it is called rich air fuel ratio .when air is more and fuel is less then it is called poor air fuel ratio.

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2. When manipulating your pedals, you should use your
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Answer:

D. left foot for the accelerator and your right foot for the brake.

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7 0
3 years ago
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