The objective of this design project was to design a fictional engine that will represent the requirements of a defined mission for an aircraft traveling from New York to London. This supersonic aircraft was designed for commercial application however the main objective was on designing and analyzing the propulsion system. The design process was split into two sections. The first part focused on designing the supersonic inlet to satisfy ambient conditions and the desired number of shocks using Oswatitsch’s Principle. The second section focused on conducting parametric analysis by evaluating the performance of the fictional engine and comparing it to a real supersonic engine.
Refer to the diagram above for visual reference of parameter values.
| Parameter | Value |
|---|---|
| M1 | 3.20 |
| M2 | 2.57 |
| M3 | 1.95 |
| M1n = M2n = M3n | 1.49 |
| β1 | 27.82° |
| β2 | 35.60° |
| β3 | 49.98° |
| θ1 | 11.90° |
| θ2 | 14.45° |
| θ3 | 17.22° |
| Po2 / Po1 | 0.932 |
| Po3 / Po2 | 0.932 |
| Po4 / Po3 | 0.932 |
| Po5 / Po4 | 0.979 |
| πrec | 0.793 |
The following diagram illustrates the key positions along the engine that will be determined using parametric analysis.
| Parameter | Value |
|---|---|
| Inlet Velocity, Ua | 944.1 m/s |
| Inlet Area, Ai | 1.00 m2 |
| To2 | 660.4 K |
| Po2 | 283.4 kPa |
| To3 | 1314 K |
| Po3 | 2494 kPa |
| To4 | 2500 K |
| Po4 | 2444 kPa |
| To5 | 2750 K |
| Po5 | 763.5 kPa |
| To6 | 2750 K |
| Po6 | 748.2 kPa |
| To7 | 2750 K |
| Po7 | 748.2 kPa |
| Exit Velocity, Ue | 3071 m/s |
| Fuel-to-Air Ratio | 0.0276 |
| Air Mass Flow Rate, ṁa | 110 kg/s |
| Fuel Mass Flow Rate, ṁf | 3.03 kg/s |
| Exit Area, Ae | 3.35 m2 |