Assignment Number 1

1. Compare and contrast the working principles, thrust production mechanisms, and typical applications of turbojet, turbofan, and turboprop engines. Include a discussion on how bypass ratio influences overall efficiency and performance in modern commercial aircraft. Support your comparison with relevant performance parameters (e.g., thrust, specific fuel consumption) from standard textbook references. 2. Explain the starting problem in supersonic inlets and describe how shock swallowing is achieved through area variation. Using diagrams and one-dimensional flow equations, analyze the effect of inlet geometry changes on inlet performance and engine operability across subsonic to supersonic flight regimes. Discuss potential losses and real-flow effects. 3. Evaluate the suitability of chemical rocket propulsion systems (solid, liquid, and hybrid) versus emerging electric propulsion options (e.g., MPD thrusters) for different space mission profiles, such as orbital insertion, deep-space exploration, and satellite station-keeping. Consider factors like specific impulse, thrust levels, propellant characteristics, heat transfer/cooling challenges, and overall vehicle performance. Recommend the most appropriate system for a sample mission (e.g., Mars cargo transfer) and justify your choice.

Case Study Assignment

1. GE Aerospace designs military jet engines using afterburners for thrust augmentation. Evaluate the thermodynamic impact of afterburning on engine efficiency, fuel consumption, and aircraft combat performance. 2. SpaceX satellites increasingly rely on electric propulsion systems. Analyze the advantages of ion/electric propulsion compared to chemical propulsion in terms of thrust, efficiency, and mission lifetime. 3. Rolls-Royce develops high-bypass turbofan engines for modern airliners. Compare turbofan and turbojet configurations and analyze how bypass ratio affects thrust, specific fuel consumption, and noise reduction.