2) Prove that the mass of gases (m) flowing in the convergent-divergent nozzle of an afterburning jet engine is expressed by 1 7 Po A 7+1 2(7- (1+5M²)VR/T Where Po, To are the total pressure and temperature at a nozzle section having an area of A For chocking conditions, the Mach number is unity at throat section (Ath), and the above relation is reduced to Y Po m = Ath RVTO

2) Prove that the mass of gases (m) flowing in the convergent-divergent nozzle of an afterburning jet engine is expressed by 1 7 Po A 7+1 2(7- (1+5M²)VR/T Where Po, To are the total pressure and temperature at a nozzle section having an area of A For chocking conditions, the Mach number is unity at throat section (Ath), and the above relation is reduced to Y Po m = Ath RVTO

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

The converging–diverging nozzle shown in Fig. P3.22expands and accelerates dry air to supersonic speeds at theexit, where p 2 = 8 kPa and T 2 = 240 K. At the throat, p 1=284 kPa, T 1 = 665 K, and V 1 = 517 m/s. For steadycompressible fl ow of an ideal gas, estimate ( a ) the mass fl owin kg/h, ( b ) the velocity V 2 , and ( c ) the Mach number Ma 2 .
1. Air, with stagnation conditions of 800 kPa and 100 °C, ex pands isentropically to a section of a duct where A₁ = 20 cm² and p₁ = 47 kPa. Compute ( a ) Ma₁ , ( b ) the throat area , and ( c ) m . At section 2 between the throat and section 1, the area is 9 cm². (d) Estimate the Mach number at sec tion 2. Plz sketch and solve it
Air enters a converging/diverging nozzle (diameters : 4mm , 2 mm 8 mm) at 1400 kpa and 200 C. the ratio of specific heats for air , k, is equal to 1.4. specific heat at constant pressure is equal to 1.03 kJ/kg·K; gas constant is 0.287 kPa·m3/ kg·K. mass flow rate is 2.5 kg/s. Find the location in meter that Mach number would equal to 2? Please explain and Show work Again Unit for answer is in meter (m)
Air flows through a duct as in Fig, where A1 =24 cm2, A2 = 18 cm2, and A3 = 32 cm2. A normalshock stands at section 2. Compute (a) the mass flow,(b) the Mach number, and (c) the stagnation pressure atsection 3.
What is the Mach number of an airflow with a velocity of 2000m/s, at 2,000 ft altitude?
The converging-diverging nozzle of the engine of a new supersonic unmanned aerial vehicle (UAV) has an exit area of 50 cm^2 . At the design operating condition, the mass flow rate of exhaust gases (? ≈ 1.4, molecular weight = 26 g/mol) is 1.75 kg/s. The exhaust gases enter the nozzle with stagnation pressure and temperature equal to Po = 300 kPa and To = 500 K, respectively a) What is the optimal cruising altitude for the operation of the nozzle of this UAV? (b) What is the lowest altitude at which the plane can fly such that the flow inside the diverging part of the nozzle is kept supersonic? Note: - Assume that the stagnation conditions of the flow of exhaust gases entering the nozzle are kept constant with varying altitude
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 lbm
Air, assumed to be a perfect gas from Table A.4, fl owsthrough a long, 2-cm-diameter insulated tube. At section 1,the pressure is 1.1 MPa and the temperature is 345 K. Atsection 2, 67 meters further downstream, the density is1.34 kg/m 3 , the temperature 298 K, and the Mach numberis 0.90. For one-dimensional fl ow, calculate ( a ) the massfl ow; ( b ) p 2 ; (c) V 2 ; and ( d ) the change in entropy between1 and 2. ( e ) How do you explain the entropy change?
A 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.
In Fig. water exits from a nozzle into atmosphericpressure of 101 kPa. If the fl ow rate is 160 gal/min, what isthe average velocity at section 1?( a ) 2.6 m/s, ( b ) 0.81 m/s, ( c ) 93 m/s, ( d ) 23 m/s, ( e ) 1.62 m/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.
Fluid mechanical A large vessel contains compressed air at To = 350 K and Po = 2 bar. A converging-diverging nozzle is attached to the vessel to discharge air. The throat area of the nozzle is 200 cm2. At the exit, the pressure is 20 kPa and the flow is supersonic. Answer the followings: The mass flow rate of the air = Mach number at exit = he exit are = Air velocity at exit Air velocity at throat = Air pressure at throat =