This repository documents the development of a conceptual scramjet engine for a hypersonic vehicle as part of the AE4321 propulsion design project. It includes performance modeling, thermodynamic cycle analysis, flow‐path development, and system‐level optimization.
Design and analyze a scramjet propulsion stage capable of sustaining hypersonic cruise (Mach 5–8) under ideal and quasi‐realistic assumptions. Deliverables include:
- Inlet total‐pressure recovery design and optimization
- Combustor fuel–air ratio and exit temperature analysis
- Nozzle sizing via NPR→Ae/At interpolation
- Cycle performance at Mach 6–8 (Isp, thrust per mass‐flow)
- Dynamic‐pressure corridor verification (q ≈ 1000–1500 psf)
- System integration notes for two‑stage to orbit
├── README.md ← (this file) ├── TO-DO.md ← Live task tracker ├── docs/ │ └── 02_Scramjet_Analysis.md ← Written report for scramjet section ├── analysis/ │ ├── test_functions/ ← Sanity‐check scripts │ │ ├ test_cycle_performance.m │ │ ├ test_dynamic_pressure.m │ │ ├ test_inlet_recovery.m │ │ └ test_oblique.m │ ├── find_cruise_altitude.m ← Altitude scan for q ≈ 1200 psf at Mach 6 │ ├── inlet_3shock.m ← 3‑shock inlet total‐pressure recovery │ ├── nozzle_data.m ← Digitized NPR vs Ae/At data + save .mat │ ├── nozzle_data.mat ← Binary data for nozzle interpolation │ ├── optimize_inlet.m ← Practical 3‑shock inlet optimizer │ ├── plot_inlet_recovery.m ← Plot inlet recovery vs Mach │ └── scram_cycle.m ← Ideal Farokhi‐style scramjet cycle ├── analysis/utils/ ← Helper functions │ ├── atmos_isa.m ← ISA atmosphere up to 85 km │ ├── M_from_AR.m ← Solve supersonic Mach from area ratio │ ├── obliqueShock.m ← Θ–β–M + normal‑shock total‐pressure ratio │ └── (optional) inlet_obj.m ← Standalone objective (can be removed) ├── figures/ ← Generated plots └── reference/ ← Supporting papers & data
- Inlet: 3‑oblique‑shock recovery, optimized for Mach 6–8
- Combustor: static exit T₄ = 4000 °R (2220 K), η_b = 0.95 → f
- Nozzle: γ=1.3 NPR→Ae/At interpolation & exit Mach solve
- Performance: Isp, thrust per mass‐flow at Mach 6, 7, 8
- Dynamic Pressure: verify q in 1000–1500 psf corridor
- Optimization: bulk deflection distribution for max worst‑case recovery
- Open MATLAB, add paths:
addpath('analysis','analysis/utils');