Date of Award
Previous research efforts at North Carolina Agricultural and Technical State University (NCAT), led to the design of a morphing RAM-SCRAMJET model with superior thrust-to-drag performance characteristics. A literature survey, conducted as part of this MS thesis effort, revealed that the morphing RAM-SCRAMJET model has many attractive engineering characteristics and is worthy of a realistic engineering evaluation. The objective of this effort is to improve on the NCAT RAM-SCRAMJET model by incorporating real-world effects into the design process. In accomplishing this goal, a quasi-one-dimensional flow field solver with capabilities of modeling the real-world effects was developed, coded in object oriented FORTRAN, and incorporated into the NCAT original model. The improved quasi-one-dimensional flow field solver is based on the Runge-Kutta 4th order method for solving systems of differential equations. In principle, the new solver allows for the flow field evaluation within arbitrary shaped ducts in which the influences of â€˜area changeâ€™, â€˜frictionâ€™, â€˜heatingâ€™ and â€˜chemistryâ€™ may be of importance. Prior to incorporating the new solver into the NCAT RAM-SCRAMJET model, a detailed validation study was conducted. These tests demonstrated that the â€˜area changeâ€™ and â€˜frictionâ€™ capabilities performed as expected. Unfortunately, the â€˜heatingâ€™ and â€˜chemistryâ€™ capabilities did not, and as such these capabilities were not added to the NCAT model. Now, with improved but limited real-world capability, the NCAT RAM-SCRAMJET model was used to conduct an updated system performance study. Engineering tests were conducted in the Mach number range of 4 through 12. Results showed the improved NCAT scramjet code performs well at low Mach numbers, but did not compare well with independent efforts in the high Mach number region. At this stage, the difference is attributed to the fact that the new flow field solver cannot predict the effects of heating.
Lawrence, Thomas, "The Inverse Design Of Hypersonic Flow Paths" (2014). Theses. 208.