Answer:
The diameter of the shaft is 80.5 mm.
Explanation:
Torsion equation is applied for the diameter of the solid shaft.
Step1
Given:
Power of the shaft is 100 kw.
Revolution per minute is 160 RPM.
Allowable shear stress is 70 Mpa.
Maximum torque is 20% more than the mean torque.
Step2
Mean torque is calculated as follows:
T=5968.31 N-m
Step3
Maximum torque is calculated as follows:
T_{max}=7161.97 N-m
Step4
Apply torsional equation for diameter of shaft as follows:
d=0.0805 m
or,
d=80.5 mm
Thus, the diameter of the shaft is 80.5 mm.
Answer:
1) This is because too much fuel is needed to get a payload from the surface to orbital altitude an accelerated to orbital speed.
2) This is because space travel present extreme environment that affect machines operations and survival.
Explanation:
Hope it helps
Answer:
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To solve this problem it is necessary to apply the concepts related to temperature stagnation and adiabatic pressure in a system.
The stagnation temperature can be defined as
Where
T = Static temperature
V = Velocity of Fluid
Specific Heat
Re-arrange to find the static temperature we have that
Now the pressure of helium by using the Adiabatic pressure temperature is
Where,
= Stagnation pressure of the fluid
k = Specific heat ratio
Replacing we have that
Therefore the static temperature of air at given conditions is 72.88K and the static pressure is 0.399Mpa
<em>Note: I took the exactly temperature of 400 ° C the equivalent of 673.15K. The approach given in the 600K statement could be inaccurate.</em>
