• Gas Turbine: Turbojet with afterburner selected via cycle parametrics (πc = 16, TT4 = 1800 K)

• Ramjet: Oblique shock inlet with multi-ramp configuration, diffuser and burner optimized for M=5

• Mission Profile: M=0.2 takeoff, M=2.5 transition, M=5 cruise over 7500 km

• Propulsion Transition: Mode handover modeled at Mach 2.5 using mass flow continuity and pressure matching constraints

• Key Analyses: Nozzle throat area sizing, burner Mach number, mass flow rate matching

• Fuel Type: JP-7 for high-temp capability; enthalpy of reaction = 43,500 kJ/kg

• Efficiencies: Gas turbine η₀ ≈ 0.45; Ramjet η₀ ≈ 0.587 (trajectory-averaged): Calculated using trajectory integration of PERF and inlet recovery data

• Used PARA for engine configuration selection and design point thrust performance

• Used PERF for off-design gas turbine analysis across Mach 0.2–2.5

• Applied 2D inlet flow analysis to optimize ramp geometry and delay shock unstarts

• Evaluated trajectory-averaged efficiency and calculated fuel and empty mass fractions

• Used Breguet range equations to determine takeoff thrust and vehicle sizing from fuel mass data

• Validated sizing using textbook Breguet range relations; matched vehicle mass and thrust to design constraints

• Takeoff mass and thrust were iterated using fuel and empty mass fractions until convergence with the empirical correlation equation

• Achieving smooth performance transition between gas turbine and ramjet propulsion modes

• Managing shock control and maintaining flow recovery across 2D inlet ramp geometries

• Ensuring mass flow continuity and pressure matching at the transition Mach number (M = 2.5)

• Iteratively adjusting burner entry Mach numbers, diffuser area ratios, and ramp angles to optimize thrust and efficiency

• Balancing design feasibility with performance metrics (e.g., nozzle sizing, throat matching, drag coefficients)

These constraints required multiple looped iterations between ramp geometry, diffuser efficiency, and nozzle area matching to meet all mission objectives.

This project was completed in a 2-person team. I contributed to:

• Gas turbine cycle configuration and off-design performance

• Engine transition sizing and trajectory-averaged analysis

• System-level mass budgeting and final report development

We delivered a trajectory-consistent TBCC propulsion solution achieving Mach 5 cruise and improved cruise efficiency through integrated multi-mode staging. Final configuration demonstrated effective performance handover between propulsion modes and compliance with system mass and range constraints.

Propulsion System Design · Turbine-Based Combined Cycle (TBCC) · Para & Perf Engine Modeling · Ramjet Inlet Optimization · Mass Fraction Analysis · Excel · Thermodynamic Trade Studies · Cycle Parametrics · Inlet Flow Simulation · Report Development

This project gave me first-hand experience with propulsion system integration across flight regimes. Working with Mattingly’s PARA and PERF tools, with hand-derived inlet and nozzle analyses, strengthened my ability to bridge theoretical models with real-world engine performance simulations. I gained deeper insight into staging transitions, flow recovery behavior, and how vehicle mass and sizing constraints drive tradeoffs in thrust, efficiency, and fuel usage.

This experience established my interest in high-speed propulsion systems and built confidence in applying design tools and workflows used in both aerospace research and industry.