Discuss the significance of Reynolds number in pressurized flow analysis ?
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Discuss the significance of Reynolds number in pressurized flow analysis ?
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- Show that for isentropic flow of a perfect gas if a pitot- static probe measures Po, p, and Tg, the gas velocity can be calculated from (k-1Vk v - 2,7, 1 - What would be a source of error if a shock wave were formed in front of the probe?What are the physical and quantitative evidence of turbulence in fluid flow?The following rheological data were collected on a new "Thick 'n Spicy" brand of tomato catsup at 20°C and 90 kPa. rate of shear (s') shear stress (Pa) 10.0 20.4 20.0 21.5 40.0 23.0 60.0 25.0 80.0 26.5 (a) Plot these measured values on graph-paper. Which class of fluid does the catsup belong to? (b) Write the appropriate model for describing the rheological behavior of "Thick 'n Spicy" catsup. Specify the numerical value(s) and the units of the associated constant(s). (c) What shear stress is expected when the rate of shear, under vigorous shaking of a bottle of "Thick 'n Spicy", is 150 s?
- For supersonic and hypersonic wind tunnels, a diffuser efficiency, ηD,can be defined as the ratio of the total pressures at the diffuser exit andnozzle reservoir, divided by the total pressure ratio across a normal shockat the test-section Mach number. This is a measure of the efficiency ofthe diffuser relative to normal shock pressure recovery. Consider asupersonic wind tunnel designed for a test-section Mach number of 3.0which exhausts directly to the atmosphere. The diffuser efficiency is 1.2.Calculate the minimum reservoir pressure necessary for running thetunnel.A flow is said to be supersonic, if the (a) If the velocity of flow is very high (b) Mach number is between 1 and 6 (c) Mach number is more than 6 (d) If the discharge is difficult to measureFor Air Assume: y =1.4 and R = 287 J/kg K Question B1 a) Air is flowing at a Mach number of 0.6 in a two-dimensional duct at a location where the area is of 0.75 m². At this location the static pressure is 50 kPa and the static temperature is 300 K. 1- Calculate the mass flow rate through the duct; [2 marks] 2- What percentage in area change would be necessary to reach a Mach number of 0.75? [2 marks] 3- What percentage in area change would be necessary to reach a Mach number of 1.00? [2 marks] b) A normal shock wave occurs in a gas with an unknown specific heat ratio. The static pressure ratio across the normal shock wave is 10.6. The Mach number downstream of the shock wave is equal to 0.495, find the specific heat ratio of the gas and the velocity ratio across the shock wave. [8 marks] c) Explain why successive infinitesimal compression waves tend to reinforce and form a shock wave. Use sketches to illustrate your answer. [5 marks] d) Show that for a choked convergent nozzle further…
- The continuity of flow equation is fundamental to much of the fluid flow in building services systems illustrate the continuity system and its associated equations.Suppose a gas flows through a constant insulated path. Parameters of temperature, pressure and mach is 520R, 50psi and 0.45 respectively. A point in the downstream calculated the mach number to equal to 1. Calculate for the temperature and pressure downstream. Methane Gas (k=1.32, R=96.4 ft-lbf/ lbm-R) 1 slug = 32.174 lbmThe following rheological data were collected on a new "Thick 'n Spicy" brand of tomato catsup at 20°C and 90 kPa. rate of shear (s") shear stress (Pa) 10.0 20.4 20.0 21.5 40.0 23.0 60.0 25.0 80.0 26.5 (a) Plot these measured values on graph-paper. Which class of fluid does the catsup belong to?
- 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 A₁2. A particle is moving in air at sea level where the temperature is 18°C. The two disturbance spheres created by the particle at points A and B are shown in the figure below. Determine the Mach no. and velocity of the particle. (Hint: For different time intervals choose the first sphere i.e. the bigger) Ans: 0.5, 171 m-s?. 9m 3m Particle <A normal shock wave propagates into atmosphere where the atmospheric temperature is equal 336K and pressure is 0.8 atm. For a given pressure ratio of p2/p₁ 41 to T₁ = a) Assuming stationary atmosphere, calculate the shock wave velocity and the velocity induced behind the shock wave. Also calculate the temperature, total pressure and total temperature of the fluid particles behind the shock wave using equations for moving normal shock. =