Carbon Dioxide (CO₂) gas flows steadily in a convergent nozzle. At section 1, flow conditions are T₁ = 400K, P₁ = 500 kPa and M₁ = 0.65. The mass flow rate at exit section (not the same as section 1), is 1.742 kg/sec. The area of cross section A₁

Carbon Dioxide (CO₂) gas flows steadily in a convergent nozzle. At section 1, flow conditions are T₁ = 400K, P₁ = 500 kPa and M₁ = 0.65. The mass flow rate at exit section (not the same as section 1), is 1.742 kg/sec. The area of cross section A₁

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

See similar textbooks

Similar questions

Each stage of an axial flow compressor is of 0.5 reaction, has the same mean blade speed and the same flow outlet angle of 30 degree relative to the blades. The mean flow coefficient is constant for all stages at 0.5. At entry to the first stage the stagnation temperature is 278 K, the stagnation pressure 101.3 kPa, the static pressure is 87.3 kPa and the flow area 0.372 m. Using compressible flow analysis determine the axial velocity and the mass flow rate.
Comment on the significance of any experimental errors for ORIFICE AND FREE JET FLOW
Each stage of an axial-flow compressor is 0.5 reaction,, has the same blade speed and the same flow outlet angle of 30 deg relative to the blades. the mean flow coeficcient is constant for all stages at 0.5. At entry to the first stage the stagnation temperature is 278 K, the stagnation pressure 101.3 kPa, the static pressure is 87.3 kPa and the flow area 0.372 m2. Using compressoble flow analysis determine the axial velocity and the mass flow rate. Determine also the shaft power needed to drive the compressor when there are 6 stages and the mechanical efficiency is 0.99.
Air, supplied by a reservoir at 450 kPa, flows through a con verging-diverging nozzle whose throat area is 12 cm². A nor mal shock stands where A1 = 20 cm². (a) Compute the pres sure just downstream of this shock. Still farther downstream, at A2 = 30 cm² estimate (b) p3, (c) A3, and (d) Ma3.
Ethanol at 20°C flows at 125 U.S. gal/min through a horizontalcast iron pipe with L= 12 m and d = 5 cm. Neglecting entranceeffects, estimate (a) the pressure gradient dp/dx, (b) thewall shear stress τw, and (c) the percentage reduction in frictionfactor if the pipe walls are polished to a smooth surface.
A simple carburetor under a certain condition delivers 5.45 kg/h of petrol with an air fuel ratio of 15. The fuel jet area is 2mm2 with coefficient of discharge of 0.75. If the tip of the fuel jet is 0.635cm above the level of petrol in the float chamber and the venturi throat coefficient of discharge of 0.80. calculate: (i) The venturi depression in cm of H2O necessary to cause air and fuel flow at the desired rate. (ii) The venturi throat diameter. (iii) The velocity of air across the venturi throat. You make take density of air = 1.29 kg/m3 and specific gravity of petrol =0.72
A Francis radial-flow hydroturbine has the following dimensions, where location 2 is the inlet and location 1 is the outlet: r2 = 2.00 m, r1 = 1.30 m, b2 = 0.85 m, and b1 = 2.10 m. The runner blade angles are ?2 = 71.4° and ?1 = 15.3° at the turbine inlet and outlet, respectively. The runner rotates at n. = 160 rpm. The volume flow rate at design conditions is 80.0 m3/s. Irreversible losses are neglected in this preliminary analysis. Calculate the angle ?2 through which the wicket gates should turn the flow, where ?2 is measured from the radial direction at the runner inlet. Calculate the swirl angle ?1, where ?1 is measured from the radial direction at the runner outlet. Does this turbine have forward or reverse swirl? Predict the power output (MW) and required net head (m).
Air with stagnation pressure of 800 kPa and temperature of 100⁰C ,is expanded isentropically to the channel 1 where A₁ = 20 cm² and P₁ 47 kPa. Count: a. Ma1 b. The area of the throat / neck (the narrow part) of the channel c. Mass flow rate m d. In part 2 which is located between the throat/neck with part 1, where the area of part 2 is 9 cm² ,calculate Ma2
Falcon 9 rocket engine, fuel mixture LOX/RP1 is combusted in a large tank and exhauststhrough a converging-diverging (C-D) nozzle. The combustion gas (k = 1.221, R = 0.3885kJ/kg.K) in the large tank has a temperature of 3500 K and pressure 9 MPa (abs). The throatdiameter of the C-D nozzle is 0.5334 m and the nozzle operates at design condition at 20km altitude. The flow in the C-D nozzle is steady and isentropic.Air pressure above sea level can be calculated as :p = 101325 (1 – H x 2.25577 x 10-5)5.25588where101325 = normal temperature and pressure at sea level (Pa)p = air pressure (Pa)H = altitude above sea level (m) Express ALL answers in 4 significant figures. (a) Calculate : Velocity at the Exit and the diameter of the EXIT.(b) Calculate the Thrust produced. Help me to solve a and b please im stuck
A blower supplies standard air to a plenum that feeds twohorizontal square sheet-metal ducts with sharp-edged entrances.One duct is 100 ft long, with a cross-section 6 in by6 in. The second duct is 200 ft long. Each duct exhausts tothe atmosphere. When the plenum pressure is 5.0 lbf/ft2(gage) the volume flow in the longer duct is three times theflow in the shorter duct. Estimate both volume flows andthe cross-section size of the longer duct.
Helium gas enters a convergent channel with T1=400oC P1=100 kPa and Ma1=0.25. Assuming the flow is steady and isentropic, find the features where the flow area decreases by 25%.
Air flows isentropically in a converging-divergingnozzle with a throat area of 3 cm2. At section 1, the pressureis 101 kPa, the temperature is 300 K, and the velocityis 868 m/s. (a) Is the nozzle choked? Determine(b) A1 and (c) the mass flow. Suppose, without changingstagnation conditions or A1, the (flexible) throat isreduced to 2 cm2. Assuming shock-free flow, will therebe any change in the gas properties at section 1? If so,compute new p1, V1, and T1 and explain.