A rigid tank of volume 0.63 m3 initially has some air inside at 0.5 bar and 300 K. A hole develops in the wall, and air from the surroundings at 1 bar, 300 K flows in until the pressure in the tank reaches 1 bar. Heat transfer between the contents of the tank and the surroundings is negligible. The final temperature is 350 K. Use the transient state entropy balcance to find the entropy generation of the process

A steam thermoelectric plant operates a Rankine cycle with overheating. Water enters the pump as saturated liquid , 7.7 kg/s. The efficiency of the pump is 0.9 The water enters the high pression turbine at 12 500 kPa and 550°C, after that steam overheats at a constant pressure of 2000 kPa until 450°C before it expands on the low pressure turbine. The efficiency of both turbines is 0.85. The vapor quality when it enters to the condenser is 0.95 Determine the thermal efficiency of the cycle.

Prepare 5 pages (max. ) brief description about Multiphase flow pumps that work at high gas volume fraction or percentage ( high GVF).

The report should address the following important points:

1- Differences between multiphase flow pump (for gas and liquid mixture) and single phase flow pump (for liquid).

2-Difference between multiphase (gas-liquid) flow pump at high gas percentage (say 80% and above gas) and a compressor.

3-Differences in pump head, pump speed, design and stages should be addressed.

4-How can we modify a single phase flow pump (liquid only) to handle gas-liquid flow

5-How can we modify a gas-liquid flow pump to handle gas percentage rather than low percentage of gas

What are the advantages and disadvantages of the PI controller, PD controller and PID controller ?

ADVANCED DYNAMICS AND CONTROL SYSTEMS

Develop a maintenance/life cycle plan for your house/car. It shall include at least 8 items that are done over the life cycle of the system and go out for at least 5 years.

A certain process requires 2.8 cfs of water to be delivered at a pressure of 30 psi. This water comes from a large-diameter supply main in which the pressure remains at 60 psi. If the galvanized iron pipe connecting the two locations is 200 ft long and contains six threaded 90o elbows, determine the pipe diameter. Elevation differences are negligible.

You are investigating two sensors to use in an experiment. Sensor A has area 600 ± 0.3 mm2 and the gap thickness is 0.3 ± 0.01 mm. Sensor B has area 400 ± 0.25 mm2 and the gap thickness is 0.2 ± 0.02 mm. Estimate the relative (hint: this is a %) and absolute uncertainties (hint: this has units of capacitance) in capacitance for both sensors. Your experiment requires that the capacitance is measured accurately within 5%. Which would you select for your experiment? Justify your response.

C = 8.85 × 10^?15 F/mm A/t

A steam generator consists of a bank of stainless stell (k=15 W/m·K) tubes habing the core configuration of CF7.0-5 and an inner diameter of 13.8 mm. The tubes are installed in a plenum whose square cross section is 0.6 m on a side, thereby providing a frontal area of 0.36 m². Combustion gases whose propertires may be aproximated as those of atmospheric air, enter the plenum at 900 k and pass in cross flow over the tubes at 3 kg/s. There are 11 rows of tubes in the gas flow direction. If saturated water at 2.455 bar experiences boiling in the tubes, what is the gas exit temperature? A convection coeficient of 10.000 W/m²·K is associated with boiling in the tubes.

AEROSPACE ENGINEERING PROBLEM

EDITED.

(20 pts) A spacecraft is launched on a mission to Mars starting from a 300 km
circular parking orbit. Calculate the departure angle, of the departure hyperbola.

May I please get some help, Thank You

A solid round bar with diameter D=1D=1 has a grove of depth e=0.1e=0.1 in, with radius r=0.1r=0.1 in, as shown in Table A-15-15. The bar is made of cold drawn steel with SUT=54SUT=54 kpsi. The bar is only subjected to reversing torque T=1.5T=1.5 klfb-in. Must carry at least 4 significant digits for everything. Estimate ff using equations, not Fig. 6-18. Knock down SUTSUT for torsion, but only AFTER calculating S?eSe? and ff; only then calculate aa, bb, and life NN with the lower SUTSUT. Use Eqs. 6-34 and 6-35b for notch sensitivity in terms of uncorrected SUTSUT and rr, not Fig. 6-21. Assume Nt=103,Ne=106Nt=103,Ne=106.
?? Calculate the endurance limit SeSe adjusted for modifying factors.
?? Calculate the reduction factor ff.
?? Calculate the intercept aa of the high-cycle fatigue line.
?? Calculate the slope bb of the high-cycle fatigue line.
?? Calculate the fatigue stress concentration KfsKfs adjusted for notch sensitivity.
?? Calculate the number of cycles NN to failure.

Two previously undeformed cylindrical specimens of an alloy are to be strain hardened by reducing their cross-sectional areas (while maintaining their circular cross sections). For one specimen, the initial and deformed radii are 16 mm and 12 mm, respectively. The second specimen, with an initial radius of 11 mm, must have the same deformed hardness as the first specimen; compute the second specimen's radius, in mm, after deformation.

The dry- and wet-bulb temperatures of atmospheric air at 98 kPa are 28 and 14°C, respectively. Determine the following values.  

1. The specific humidity in  kg H₂O/kg dry air

2. The relative humidity in %

3. The enthalpy of air in  kJ/kg dry air

Consider a light, single-engine, propeller-driven, private airplane, approximately modeled after the Cessna T-41A. The characteristics of the airplane are as follows: wingspan = 35.8 ft, wing area = 174 ft², normal gross weight = 2950 lb, fuel capacity = 65 gal of aviation gasoline, the parasite drag coefficient C_D,0 = 0.025, Oswald efficiency factor = 0.8 and propeller efficiency = 0.8. The power plant comprises one-piston engine of 230 hp at sea level. Calculate the maximum velocity of the airplane at sea level.

Consider an airplane patterned after the Beechcraft Bonanza V-tailed, single-engine light private airplane. The characteristics of the airplane are as follows: aspect ratio = 6.2, wing area = 181 ft², Oswald efficiency factor = 0.91, weight = 3500 lb, and zero-lift drag coefficient = 0.027. The airplane is powered by a single piston engine of 345 hp maximum at sea level. Assume the power of the engine is proportional to free-stream density. The two-blade propeller has an efficiency of 0.83. Estimate the sea-level liftoff distance for the airplane. Assume a paved runway and C_L,max = 1.1 during the ground roll. When the airplane is on the ground, the wings are 4 ft above the ground.

Consider an airplane patterned after the Fairchild Republic A-10, a twin-jet attack aircraft. The airplane has the following characteristics: wing area = 47 m², aspect ratio = 6.5, Oswald efficiency factor = 0.87, weight = 103,047 N, and zero-lift drag coefficient = 0.032. The airplane is equipped with two jet engines with 40,298 of static thrust each at sea level. The thrust-specific fuel consumption is 1.0 N of fuel per Newton of thrust per hour. The fuel capacity is 2800 gal, and the maximum gross weight is 136,960 N. Calculate the range and endurance at a standard altitude of 8 km, where ?_? = 0.526 kg/m³.