) Prob 1.) Consider a quasi-1-D steady adiabatic flow of 100 kg/s of neon gas (a monatomic gas that is calorically perfect) confined in a converging-diverging nozzle. A normal shock occurs at the nozzle exit plane at (2)→ (3) as shown. Friction is insignificant.

Problem 2.) SELECT THE BEST RESPONSE Given: These equations are valid for 1-D SSSF with no external heat transfer and no external work for a calorically perfect gas with constant R, Cv, Cp & y. CIRCLE the best response (A, B, C or D) concerning the validity of each equation for other types of matter.

Problem 3) For quasi-1D steady adiabatic flow in a converging-diverging channel with negligible friction, show that the maximum achievable mass flux (m/A) occurs at "critical" or sonic flow with Mach number equal to one, valid for all simple compressible substances. Note: For steady quasi-ID flow the maximum mass flux must occur at the minimum flow area (So dA-0). Clearly show symbolic equations. Starting from fundamental principles, explain the logical and algebraic steps to show the requirement for Mach number equal to one at this critical condition. You may refer to the text but do not use derived expressions from the text to skip over fundamental

Page 4) Given: Steady-state-steady-flow of a compressible gas. A thin normal shock occurs and is shown for a control volume fixed on the wave. Relative flow at (1) approaches the shock from upstream and uniform relative flow at (2) movies away downstream of the shock. For this flow situation only the pressures and densities are known. The gas is not thermally perfect. Starting from 1st principles develop the following general relationship for the shock speed of a wave moving into a static fluid. This is the shock speed (left-right) viewed from the ground.

3. The figure indicates a hypothetical one-dimensional supersonic inlet installed in a wind tunnel and equipped with a throttle valve by which the downstream static pressure p: might be varied. Suppose that the inlet is designed for a Mach number M-3.0 and that with this flight Mach number the shock has been swallowed and an internal shock exists, as at. Neglecting all losses except those occurring in the shock, calculate and plot the shock Mach num- ber M, and the stagnation pressure ratio Puz/pa. as a function of the static pressure ratio p/p. (for y=1.4). Let p/p. range from unity to well beyond that value which disgorges the shock.

5. Sketched are three supersonic inlets: an isentropic inlet, the Kantrowitz- Donaldson inlet of Fig. 6.10, and a simple normal shock inlet. For flight Mach numbers M from 1 to 4, calculate the plot poz/Po as a function of M. with each inlet operating with best back pressure.

6. It was shown that, during starting, an isentropic diffuser would experience a detached shock and consequent losses. In order to swallow the shock, a fixed- geometry diffuser must be overspeeded. However, as shown in Fig. 6.9, as the design Mach number increases, the required overspeeding increases very rapidly, so that even if the aircraft could be infinitely overspeeded, the design Mach number would be limited to a finite value. Assuming one-dimensional flow and constant y (1.4), determine the absolute maximum design Mach number for which an otherwise isentropic diffuser of fixed geometry may be expected to start, any amount of overspeed being possible.

5. (15 pts) During actual expansion and compression processes of gases, pressure and volume are often related by PV" = C (where n and C are constants. Such processes are called Polytropic Processes.) In a certain system under study, air goes through such a polytropic process where the temperatures and pressures change from 325 K and 125 kPa to 500 K and 300 kPa respectively. Find the polytropic exponent n and the mass specific work in the process.

4. (15 pts) Initially, 1.361 kg of steam is contained in a piston-cylinder device at 260°C with a quality of0.7. Heat is added at constant pressure to allow for expansion while all of the liquid is vaporized. The steam then expands adiabatically at constant temperature to a pressure of 2758 kPa, behaving essentially as an ideal gas. Determine the work done BY the steam ON the piston. Determine the work done BY the piston ON the atmosphere. What is the useful amount of mechanical work produced in this process?

An oil pump is drawing 35 kW of electric power while pumping oil with p= 860 kg/m³ at a rate of 0.1 m³/s. The inlet and outlet diameters of the pipe are 8 cm and 12 cm, respectively. If the pressure rise of oil in the pump is measured to be 400 kPa and the motor efficiency is 90 percent,determine the mechanical efficiency of the pump.

Consider 5 kg of air initially at 101.3 kPa and 38°C.Heat is transferred to the air until the temperature reaches 260°C. Determine the change of internal energy, the change in enthalpy, the heat transfer, and the work done for (a) a constant-volume process and(h) a constant-pressure process. Use SI units.

An insulated container, filled with 10 kg of liquid|water at 20°C, is fitted with a stirrer. The stirrer is made to turn by lowering a 25-kg object outside the container a distance of 10 m using a frictionless pulley system. The local acceleration of gravity is9.7 m/s². Assume that all work done by the object is transferred to the water and that the water is incompressible. A. Determine the work transfer (kJ) to the water. B. Determine the increase in internal energy (kJ) ofthe water. C. Determine the final temperature (°C) of thewater. D. Determine the heat transfer (kJ) from the waterrequired to return the water to its initialtemperature.

The production history and fluid properties as a function of time and average reservoir pressure from the X-sand Gas reservoir in Algeria are given in the table below. The reservoir's believed to be under the influence of water drive which is entering the reservoir at a constant unknown rate (Qw) where We = (Qw)(t) and t is the time. The reservoir temperature's 160 °F. The gas gravity is 0.625 and it contains 5 mol % CO₂ and 4 mol% H₂S. Calculate the initial gas-in-place (G₁) in SCF. \text { What is the value of } Q_{w} \text { in } M \mathrm{ft}^{3} / \text { day? } Calculate the amount of water which encroached the reservoir (We) in bbl after 730 days.

9. Write types of steam trap operation by Temperature Balance

1. Consider the duct system connected to an air tank like the one shown in the figure. The system stationary discharges to the atmosphere at 101,325 kPa. Except for the indicated section, heat interactions can be neglected along the air path between the tank and the discharge. Friction effects can be neglected in all sections except the section where a length L is defined, and a friction factor is provided. No other internal irreversibility occurs in any of the pipelines. Relevant data for the solution of the problem are included in the image. a. Determine the temperature, in K, the velocity, in m / s, and the Mach number, at points 2 and 3 Determine the length, in cm, of the duct 2-3 Determine the Mach number, the velocity, in m/s, the local density, in kg / m3, at point 4Ma₁ = d. Determine the magnitude and direction of the heat transfer rate (output or input), in kW, induct 3-4 e. Determine the pressure, in kPa, at points 4, 3, and 2 f. Determine the pressure in the air tank, in kPa g. Determine the entropy ratio generated from the tank to the discharge, in W/K

(10 marks)A 0.040612 m3 tank contains 3.0 kg of water vapors at 373.95 °C. Determine the pressure of the water vapors in MPa,using: (a) The ideal-gas equation, (b) The generalized compressibility chart