2. Air is supplied to a converging nozzle from a large reservoir where the temperature and pressure are 400 K and 100 kPa, respectively. At a certain cross-section, the temperature and pressure are measured to be 383.8 K and 63 kPa, respectively. Assuming isentropic flow, find the Mach number at this cross- section and the mass flow rate per unit area. (Ans: 0.46, 103.3 kg-s1-m²).

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Air flows in a constant-area duct as shown in the figure. Assume Rayleigh line flow and the air to behave as a perfect gas with constant specific heats. For choked duct, determine: 1. Mach number at inlet (M1) 2. Stagnation temperature at inlet (To1) 3. Critical stagnation temperature (T.") 4. Mass flow rate 5. Heat input to choke the duct (q). q =? Vi = 100 m/s T1 = 320 K P1 = 200 kPa d = 1.5 cm

For non-isentropic constant-area flow with stagnation temperature change the following relation was determined: Y 1 To _ ²(y + 1)M² (1 + ¹ Z ¹ M²) 2 TO (1+yM²)² It is possible to use the above equation and calculate the downstream Mach number without resorting to iteration for a flow where the upstream Mach number, as well as the upstream and downstream stagnation temperatures, are known. This is a common calculation for flows through engine combustors. Presuming the left side is a known quantity, show that the above equation can be directly solved as a quadratic in M² and which roots correspond to the subsonic/supersonic solution. Rewrite the equation as: aM4 + bM² + c = 0, and then M² = (−b ± √b² - 4ac)/2a. Determine the appropriate expressions for a, b, and c.

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i need the answer quickly

Air is flowing in a convergent nozzle. At a particular location within the nozzle the pressure is 280 kPa, the stream temperature is 345 K. and the velocity is 150 m/s. If the cross-sectional area at this location is 9.29 x 103 m², find: (a) The Mach number at this location, (b) The stagnation temperature and pressure. (c) The area, pressure, and temperature at the exit where M-1.0. (d) The mass rate of flow for the nozzle. Indicate any assumptions you may make and the source of data used in the solution.

(b) Air flows through a cylindrical duct at a rate of 2.3 kg/s. Friction between air and the duct and friction within air can be neglected. The diameter of the duct is 10cm and the air temperature and pressure at the inlet are T₁ 450 K and P₁ = 200 kPa. If the Mach number at the exit is Ma2 determine the rate of heat transfer and the pressure difference across the duct. The constant pressure specific heat of air is cp = 1.005 kJ/kg-K. The gas constant of air is R = 0.287 kJ/kg-K and assume k = 1.4. -

Q.2. Air flows through a constant-area duct is connected to a reservoir at a temperature of 500°C and a pressure of 500 kPa by a converging nozzle, as shown in Figure. Heat is lost at the rate of 250 kJ kg. Determine the exit pressure and Mach number and the mass flow rate for a back pressure of 0 kPa. q- 250 kJkg P = 500 kPa T,= 500°C Ps = 0 kPa D=0.02m

It is required to expand 3 kg/s of air from stagnation conditions of 200kPa, 500K through a convergent-divergent nozzle to give an exit Mach No. of 2.5. Determine: (i) throat area (ii) exit pressure (iii) exit temperature (iv) exit velocity (v) exit area Ans: 0.0083m², 11.7kPa, -51°C, 747m/s, 0.0219m?