This project models the steady-state behavior of three different types of aircraft engines: turbofan, turbojet and ramjet. It allows the study of their performance at different operating conditions.
The steady-state behavior is modeled by thermo-dynamic equations which provide, for example, the temperature and pressure observed in each stage of the engine. As the stages may vary depending on the engine type, there are different sequences of transformations for each type of engine. The figure below was copied from the class notes of Prof. Pedro Lacava from Instituto Tecnológico de Aeronáutica (ITA).
The files named turbofan.m, turbojet.m and ramjet.m contain functions which return the parameters of theses engines (there are geometric and physical parameters).
This implements a thermodynamic model for three different aeronautical engines: turbofan, turbojet and ramjet. It models the steady-state behavior of the engine.
This is a function which implements the ISA atmosphere model. It returns the standard air density, temperature and pressure for a given altitude.
The following files are Matlab scripts which can be run independently:
simulate_engine.m: This calls the engine function to simulate the steady-state of any of the engine types. Upon running this script, user is prompted to choose a specific engine type and operating conditions (aircraft mach number and flight altitude). It prints the result of simulation as below.
T02: 606.6200
P02: 245.2238
T03: 1.6812e+03
P03: 7.3567e+03
T04: 1600
P04: 7.3567e+03
TET: 0
PET: 0
T05: 525.4201
P05: 29.2655
T06: 525.4201
P06: 29.2655
T08: 606.6200
P08: 245.2238
u_s: 591.0395
u_sf: 0
f: -0.0021
f_pq: 0
u: 887.1293
T_ma: -0.2973
TSFC: 0.0070performance_per_flight_phase.m: This displays a graph with a performance comparison between turbojet and turbofan engines for different flight phases (takeoff, climb and cruise). The performance is measured in terms of TSFC and specific thrust (one is the inverse of the other).
