1. For ramjet, scramjet and turbojet engines, first expression for propulsiveefficiency:Mp2uTma[(1 +ƒ)u² − u²]If the nozzle is unchoked (pe= pa) and the fuel-to-air ratio (f) is negligible.Prove that:uTuT+1/me(ue - u)е=21+ (ue/u)

Given: Inlet velocity = u Exit velocity = ue Thrust = T

Answered: 1. For ramjet, scramjet and turbojet…

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

Question C . Options A. Subsonic Nozzle B. Expansion Tube C. Diffuser D. Supersonic Nozzle
4Air enters the compressor of a simple gas turbine at p1 = 14 lbf/in2, T1 = 520°R. The isentropic efficiencies of the compressor and turbine are 83 and 87%, respectively. The compressor pressure ratio is 12 and the temperature at the turbine inlet is 2500°R. The volumetric flow rate of the air entering the compressor is 9000 ft3/min. Use an air-standard analysis. a) Determine the net power developed, in Btu/h. b) Determine the thermal efficiency of the cycle. c) The temperatures at the compressor and turbine exits in °R. d) The temperatures at the compressor and turbine enters in °R rmine the net power developed, in Btu/h .
A turboshaft engine comprising a gas generator and a free power turbine is selected to provide propulsive power for a helicopter. The helicopter is hovering in ISA conditions at an altitude of 4100 feet. The following data applies to this engine at this static max power operating point. Intake mass flow: 8.9 kg/s Compressor pressure ratio: 24.5 Compressor isentropic efficiency: 88% Mechanical efficiency: (HP & PT shaft) 99% Combustion chamber pressure loss Combustion chamber inlet pressure 4% Combustion efficiency 98.8% Combustion chamber exit temperature: 1585K Gas generator turbine isentropic efficiency: 92% Power turbine isentropic efficiency: 90% The effects of the intake and exhaust ducts may be ignored. It may be assumed that for: Air: Cp = 1.005 kJ/kg • K, y = 1.4, R = 0.287 kJ/kg • K Combustion gases: Cp = 1.148kJ/kg • K, y = 1.333, R = 0.287 kJ/kg • K A 6% direct bleed of air from the exit of the compressor is…
Air gas expands isentropically through a converging nozzle from a large tank at 150 lbf/in2, 600°R, and discharges into a region at 50 lbf/in2. The exit flow area is 1 in2. For air, use Cp = 0.24 Btu/lb.R. Determine the pressure at the exit, in lbf/in2.
During the compression stroke of a certain gasoline engine, the pressure increases from 1.00 atm to 19.0 atm. The process is adiabatic and the air-fuel mixture behaves as a diatomic ideal gas. (a) By what factor does the volume change? Vfinal = Vinitial (b) By what factor does the temperature change? Tinal = Tinitial Assume the compression starts with 0.016 mole of gas at 28.5°C. (c) Find the value of Q that characterizes the process. (d) Find the value of AEnt that characterizes the process. (e) Find the value of W that characterizes the process.

Recommended textbooks for you

Elements Of Electromagnetics

Mechanical Engineering

ISBN:

9780190698614

Author:

Sadiku, Matthew N. O.

Publisher:

Oxford University Press

Mechanics of Materials (10th Edition)

Mechanical Engineering

ISBN:

9780134319650

Author:

Russell C. Hibbeler

Publisher:

PEARSON

Thermodynamics: An Engineering Approach

Mechanical Engineering

ISBN:

9781259822674

Author:

Yunus A. Cengel Dr., Michael A. Boles

Publisher:

McGraw-Hill Education

Elements Of Electromagnetics

Mechanical Engineering

ISBN:

9780190698614

Author:

Sadiku, Matthew N. O.

Publisher:

Oxford University Press

Mechanics of Materials (10th Edition)

Mechanical Engineering

ISBN:

9780134319650

Author:

Russell C. Hibbeler

Publisher:

PEARSON

Thermodynamics: An Engineering Approach

Mechanical Engineering

ISBN:

9781259822674

Author:

Yunus A. Cengel Dr., Michael A. Boles

Publisher:

McGraw-Hill Education

Control Systems Engineering

Mechanical Engineering

ISBN:

9781118170519

Author:

Norman S. Nise

Publisher:

WILEY

Mechanics of Materials (MindTap Course List)

Mechanical Engineering

ISBN:

9781337093347

Author:

Barry J. Goodno, James M. Gere

Publisher:

Cengage Learning

Engineering Mechanics: Statics

Mechanical Engineering

ISBN:

9781118807330

Author:

James L. Meriam, L. G. Kraige, J. N. Bolton

Publisher:

WILEY

SEE MORE TEXTBOOKS

1. For ramjet, scramjet and turbojet engines, first expression for propulsive efficiency: Mp 2uT ma[(1 +f)u² − u²]|| If the nozzle is unchoked (pe= pa) and the fuel-to-air ratio (f) is negligible. Prove that: uT 2 uT + 1/me(ueu)² 1 + (ue/u) =