Abstract

Abstract : The Method of Characteristic (MOC) Nozzle Flowfield Solver code is a structured, Two-Dimensional (2-D), isentropic supersonic flow solver for rocket nozzle problems. The code uses a marching step method based on a second order modified Euler predictor/corrector scheme with iteration. The initial starting line is determined either by a user-input profile or by Sauer s method for determining the sonic line. Initial wall options include a starting circular arc that can be followed by a second order quadratic wall based on user inputs. The remaining downstream wall is then determined by the local characteristic and mass flow rate. A simple boundary-layer correction using a one-eighth power law is used to determine the viscous corrected shape. The software coding is written in Fortran 90. Input files are used to transfer information to the program.

Talk to us

Join us for a 30 min session where you can share your feedback and ask us any queries you have

Schedule a call

Disclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.