Method of Characteristic (MOC) Nozzle Flowfield Solver - User's Guide and Input Manual

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.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 2013
Accession Number
ADA578559

Entities

People

  • Kevin D. Kennedy

Organizations

  • United States Army Research, Development and Engineering Command

Tags

Communities of Interest

  • Air Platforms
  • C4I
  • Energy and Power Technologies
  • Weapons Technologies

DTIC Thesaurus Topics

  • Axisymmetric Flow
  • Boundaries
  • Boundary Layer
  • Computer Programs
  • Flow
  • Flow Fields
  • Flow Rate
  • Mach Number
  • Mass Flow
  • Operating Systems
  • Radial Velocity
  • Shape
  • Stagnation Pressure
  • Stagnation Temperature
  • Static Pressure
  • Throat
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Computational Fluid Dynamics (CFD)
  • Computer Science.
  • Fluid Dynamics.

Technology Areas

  • Hypersonics