A normal shock is positioned in the diverging portion of a frictionless, adiabatic, converging- diverging air flow duct where the cross sectional area is 0.0093 [m²] and the local Mach number is 2.0. Upstream of the shock, the stagnation pressure and temperature are 1379 [kPa] and 394[°C] The duct exit area is 0.014[m²], Determine: a) the exit Mach number b) exit temperature, c) exit pressure d) duct exit mass flow rate and e ) thrust.

A normal shock is positioned in the diverging portion of a frictionless, adiabatic, converging- diverging air flow duct where the cross sectional area is 0.0093 [m²] and the local Mach number is 2.0. Upstream of the shock, the stagnation pressure and temperature are 1379 [kPa] and 394[°C] The duct exit area is 0.014[m²], Determine: a) the exit Mach number b) exit temperature, c) exit pressure d) duct exit mass flow rate and e ) thrust.

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

A) A fuel injection nozzle creates small droplets of liquid gasoline at 15.6 C. If the average diameter of the droplets is 350 (Greek mu)m, what is the difference in pressure between the inside and outside of the droplets? ( (Greek mu)m = 10^-6 m) B) What is the difference between the pressure inside a soap bubble and atmospheric pressure for a 3-in. diameter bubble? Assume that the surface tension of the soap film is equivalent to 70% of that for pure water at 60 F.
In the United States, electricity is sold using the SI units of kilowatt (kW) or megawatt (MW), and fuel for power generation stations is generally purchased using English units, e.g., British thermal unit (Btu), gallon (gal), and ton. An industrial power plant has an average annual load of 100 MW (electrical). If the overall thermal efficiency is 33% (based on HHV), what is the annual cost of fuel if the plant is fired with (a) natural gas, (b) No. 2 fuel oil, and (c) bituminous coal? Use the data from Tables 2.2, 2.7, and 2.13. Assume the cost of natural gas is $5/million Btu, the cost of No. 2 fuel oil is $3/gal, and the cost of bituminous coal is $60/ton (1 ton = 2000 lbm)
5. Consider a Pitot probe in high-speed flow.(c) You are flying through air at static p∞ = 0.8 atm [abs]. Your velocimeter broke,but you are still receiving the following direct stagnation pressure readings (atm[abs]) from the Pitot probe mounted on your aircraft’s noise: i) 3.152 ii) 1.357 iii) 38.428 iv) 0.8 Find the freestream Mach number corresponding to each of the pressure readings. (d) If we are to believe reading (iv), can we step out of the aircraft safely? Why?
On October 3, 1967, pilot William J. "Pete" Knight set a world record that still stands to this day for the fastest flight by a crewed, powered aircraft by flying the North American Aviation X-15 as fast as Mach 6.7 at an altitude of 102,000 ft above sea level. Mach number is the ratio of an object’s velocity to the local speed of sound. Using the table for atmospheric properties with respect to altitude, calculate the speed of sound at an altitude of 100,000 ft. What must have been the velocity of the X-15?
The speed of a supersonic aircraft flying at an altitude of 1,100 meters corresponds to a Mach number of 2.5. Estimate the time elapsed, in seconds, between the instant the aircraft was directly over head of an observer and the instant the observer feels the disturbance due to the aircraft. Presume that the temperature at the given height is 280°K, with k = 1.4 and R = 2.87 J/kg·K, in determining the questions of the following three cases: A) When the observer is stationaryB) When the observer is moving in the direction of the aircraft at M = 0.5C) When the observer is moving in the opposite direction with M = 0.5.
A high-flying jet cruising at 3000km/hr displays a Mach Number of 3.2. What is the speed of sound and the temperature of the air at that altitude?
An A380 is observed flying at 25,000 ft with a speed of 300 fps in the standard atmosphere. What is the Mach Number?
Q#01: Explain the following terms in your own words. Mach Number. Sub-Sonic. Angle of Attack. Thrust Chord Line. Drag Coefficient. Pitch Moment. Wind Tunnel. 10. Skin Drag.
Which of the following statement is NOT correct about the Mach number? If the Mach number value is between 0.8 and 1.2, then the flow is supersonic. The internal duct flow analysis mainly depends only two types of flow, supersonic and subsonic flow. If the Mach number value is between 0.3 and 0.8, then the flow is subsonic. Density effects are negligible for Mach number less than 0.3.
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.
Suppose we got the following data during a test of a 2- stroke engine in which gas is usedas a fuel:Diameter of the piston = 149 mmStroke length = 179 mmClearance volume = 0.88 literrpm of the engine = 302Indicated mean effective pressure = 6.0 barGas consumption = 6.0 m3/hCalorific value of the gas (fuel) = 16990 kJ/m3Make a clear sketch the geometry of this engine using the data and determine thefollowing:i. Indicated power developed by the engine in watt.ii. Air Standard Efficiencyiii. Indicated thermal efficiency of the engine.
Consider a cone at zero angle of attack in a hypersonic flow. (Hypersonic flow is very high-speed flow, generally defined as any flow above a Mach number of 5.) The half-angle of the cone is θc, as shown inthe figure. An approximate expression for the pressure coefficient on the surface of ahypersonic body is given by the newtonian sine-squared law : Cp = 2 sin2 θcNote that Cp, hence, p, is constant along the inclined surface of the cone. Along the base of the body, we assume that p = p∞. Neglecting the effect of friction, obtain an expression for the drag coefficient of the cone, where CD is based on the area of the base Sb.