A MATLAB® MODEL FOR THE DESIGN AND OPTIMIZATION OF RAMJET ENGINES USING CALORICALLY IMPERFECT GASES

Open Access
Author:
Nunez, Marco
Area of Honors:
Mechanical Engineering (Behrend)
Degree:
Bachelor of Science
Document Type:
Thesis
Thesis Supervisors:
  • Barukyah Shaparenko, Thesis Supervisor
  • Dr. Yi Wu, Honors Advisor
Keywords:
  • Ramjet
  • Rayleigh-flow
  • Taylor-Maccoll
  • Supersonic
  • Normal shock
  • Oblique shock
  • Matlab
Abstract:
A calorically imperfect, thermally perfect gas model is applied to supersonic flow in order to solve the governing equations for flow in normal shocks, oblique shocks, flow over a cone (Taylor-Maccoll), and flow with heat addition. Each of these types of flows is then used in the context of a ramjet engine in conjunction with ideal models of nozzles and diffusers in order to determine the air properties at each of the different stations inside the engine. The main objective being to develop techniques to optimize the vehicle’s overall performance. A description on how to increase efficiency is provided, then, using MATLAB® as the chosen computer package, a case study is performed on Lockheed Martin’s Kingfisher drone to validate the procedures used and compare the results with known values for a calorically perfect gas model. Specified parameters for the optimization are the inlet angle, combustion chamber heat addition, generated thrust, and specific impulse.