Gas Flows in Rocket Motors. Volume 3. Appendix D. Computer Code Listings
Abstract
Detailed descriptions of the governing equations, the method of solution, and the computer code for calculating perfect gas or real gas flow in axisymmetric nozzles are given. The codes permit calculation of a perfect gas or a real gas for inviscid flow by solving the Euler equations, and for viscous flow by solving the thin layer Navier-Stokes equations. These equations are written in a conservative form and solved implicitly in body-fitted coordinates. The solution obtained by the conservative variables is expressed in terms of the density, rho, the momentum parallel to the axis of symmetry (rho(u)), the momentum perpendicular to the axis (rho(v)), and the total internal energy, e(o) . These variables are then used to calculate the nonconservative primitive variables, the velocity components, u and v, the pressure, p, and the temperature, T. The nozzle performance including the rate of mass flow, m, the thrust, T, and the specific impulse are also computed. The codes were written in FORTRAN V and ran on the CYBER 180/840, NOS/BE system which limited the number of grid points to 20 x 44 for solving the Euler equations and 60 x 40 for the TLNS equations. The results obtained for the nozzle flowfield showed maximum global mass flux errors of less than + or - 1% for the Euler equations and less than + or - 2% for the TLNS equations. Solutions with more dense grids (typically 100 x 50 or higher) consistently showed global mass conservation of better than one percent. (aw)
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1989
- Accession Number
- ADA213350
Entities
People
- Charles L. Merkle
- Chau Lyan-chang
- Yigal Kronzon
Organizations
- Leidos