Assignment # 2 AE4451

Form teams of 2 each.

Develop a computation routine which can analyze the performance of a specified jet engine at a given flight altitude and Mach number. This routine should be able to handle any type of engine from ramjet to turboprop.

Technology assumptions

Engine type	Subsonic ramjet	scramjet	Turbofan	Turboprop
Subsonic diffuser Pressure recovery factor	0.9	N/A	0.9	0.9
Compressor polytropic efficiency			0.925	0.925
Turbine inlet temperature			2100K	2100K
Max duct wall temperature	2500K	2500K	2100K	N/A
Burner Pressure Recovery Factor	Rayleigh line	Rayleigh Line	0.95	0.95
Nozzle Efficiency	0.99	0.99	1.00	1.00
Max Nozzle Exit dia (supersonic)	Same as Inlet Area	Same as Inlet Area	1.2 times inlet area	N/A
Limiting throat area	Variable upto Inlet / duct area.	Variable upto Inlet / duct area.	Variable upto 0.1 times inlet area at turbine exit; variable upto inlet area at afterburner throat

Stage 1: (target: Feb. 17)

Couple the ramjet engine to the inlet / combustor work that you have already done in Assgt. 1.

Assume that the supersonic-combustion ramjet uses hydrogen fuel and the subsonic-combustion ramjet uses aviation jet fuel JP-4 (find the heating value of hydrogen-air and JP-4/air)

Find Thrust per unit air mass flow rate (m/s) and TSFC (in “per hour”) as functions of altitude and Mach number. Compare the overall results for the subsonic and supersonic combustion ramjets.

Stage 2 (target: Feb. 20)

Do the same for the turbofan and turboprop engines – the turbofan for Mach 0 to 3, and the turboprop for Mach 0 to 0.8