9 Derive Equation 7.16, which gives the relationship between the nozzle loss coef- ficient , and nozzle velocity coefficient C (7.16)
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- a) A convergent nozzle with a given area ratio is supplied with air at a constant stagnation pressure Poand a constant stagnation temperature To. With the aid of a sketch plot the nozzle mass flow rate as a function of pressure ratio () across P the nozzle. In your answer indicate the critical value of the pressure ratio. For air you may assume y = 1.4 and R = 287J/kg K. b) The engine of a supersonic aircraft is equipped with a convergent-divergent nozzle. A A, A -4.0).Determine the design subsonic and supersonic Mach numbers for this area ratio. You may assume the combustion products have the same properties as air and the expansion process through the nozzle is isentropic. The nozzle's area ratio is ( c) Determine at what pressure ratios ( ) a normal shock wave appears in the P divergent part of the nozzle at a location where -3.0) Aheck A₁A typical carbon dioxide tank for a paintball gun holdsabout 12 oz of liquid CO2. The tank is fi lled no more thanone-third with liquid, which, at room temperature, maintainsthe gaseous phase at about 850 psia. (a) If a valve isopened that simulates a converging nozzle with an exitdiameter of 0.050 in, what mass fl ow and exit velocityresults? (b) Repeat the calculations for helium.The Mach no. of a fixed geometry inlet at overspeeded for starting mode (Ai= 0.13 m2, ,At= 0.095 m2) 0.41 O 2.77 O 1.72 O 0.49 O
- In Figure below, CO2 at 25°C is flowing through the duct. Stagnation pressure at section-1, P1 = 140 kPa and the manometer fluid is oil (SG = 0.85). Neglect losses. (a) Estimate the pressure at section-2, P2. (b) Calculate the velocity at section-2 and the volume flow rate of CO2. Given: Gas constant for CO2, R = 189 J/kg.K; Density of water, pwater = 1000 kg/m³. Show all calculations. D2 = 6 cm D; = 10 cm 12 cmDerive the following equation and draw the shape of nozzle and diffuser for subsonic, sonic and dA supersonic flow. de (1-M) pcSteam which is at a pressure of 3 Bar ond dry saturoteu expands in a convergent nozzie to a pressure of 2 Bar. The area of throat is 3 cm. Negiecting approach velocity, calculate the exit velocity and mass fiow rate if (a) Equilibrium flow is assumed (b) Supersaturated flow is assumed.
- Please show your complete solution. Thank you! Air flows in a steady flow manner through a converging tube. At the inlet the pressure is 690kPaabs and the density is 0.838 kg/cu.m. If air enters with a volume flow of 125 cu.m per min at the rate of 94 m/min and the exit section has a diameter of 350mm, determine a.) the mass flow rate, kg/min b.) the diameter of the entrance section and c.) the exit velocity. Assume that the density is constant.A compressed Air enters a convergent-divergent nozzle, at 4.0 atm, 300 K and at Mach 2.0. The nozzle is fitted at the exit of a 0.3 m constant diameter pipe and 2.0 m long that supplies the air. Assuming that the friction factor for the pipe is 0.003, and that a normal shock occurs in the pipe at Mach number 1.8, a) Find the length of the pipe between the location of the normal shock and the inlet of the nozzle. b) Claculate the throat and the exit plane diameters of the nozzle if the mach number at the exit plane is 2.0 c) Calculate the exit pressure. d) On a graph, skecth the variation of static and stagnation pressure along the pipe and the nozzle.A converging–diverging nozzle exits smoothly to sealevelstandard atmosphere. It is supplied by a 40-m3 tankinitially at 800 kPa and 100 °C. Assuming isentropicflow in the nozzle, estimate (a) the throat area and(b) the tank pressure after 10 s of operation. The exitarea is 10 cm2.
- A large tank at 500 K and 165 kPa feeds air to a convergingnozzle. The back pressure outside the nozzle exit is sealevelstandard. What is the appropriate exit diameter if thedesired mass fl ow is 72 kg/h?Example 2. A high-speed AC 130 gunship is flying at a pressure altitude of 10 km. A Pitot tube on the wingtip measures a pressure of 4.24 x 10ª N/m2. Calculate the Mach number at which the aircraft is flying. Solution: Solving for P1 at an altitude of 10000 m, we get 2.65 x 104 N/m2 k-1 1.4-1 Po k 4.24 x 104) 1.4 M? k – 1 - 1 - 1 1.4 – 1 2.65 x 104 M? = 0.719 M1 = 0.848For solution of this problem also sketch velocity triangles and label it. A rotodynamic impulse turbine was used to develop power. In an impulse stage the mean diameter of the blade ring is 900 mm and the speed of rotation is 3500 1.p.m The nozzle angle is 22º and the steam exits from the nozzles with a velocity of 350 m / s. Assuming the blade velocity coefficient as 0.85 and also suppose that the blades are symmetric When the axial thrust on the blades is 150 N. Determine the power developed.