Computer Codes

As a service to the propulsion community, ERG provides distribution and support services for many of the Government sponsored propulsion computer codes, colloquially known as the “JANNAF” codes, as well as some newer Government codes including SOCRATES-P and SPIRITS.

These computer codes are available to all U.S. Government Agencies and their U.S. contractors, and are restricted by U.S. export control regulations. Interested organizations must complete an application process through ERG.

Questions on code availability and requests for distribution should be made to ERG at (410) 992-7300, and technical questions can be referred to Nick Keim at (410) 992-9950 ext. 229.


CELMINT 6.05
Combined Eulerian Lagrangian Multiphase Implicit Navier-Stokes Time-Dependent (CELMINT) Code

Platforms: UNIX, source included

The Combined Eulerian Lagrangian Multiphase Implicit Navier-Stokes Time-dependent (CELMINT) code simulates viscous flows with or without chemical reactions in 2D or 3D problems. This version is geared towards solid rocket motor internal flowfield applications and includes a two-phase flow capability.

CHAMP 2.2.3
Composite Hardbody and Missile Plumes (CHAMP) Code

Platforms: UNIX, PC (cygwin)

The Composite Hardbody and Missile Plumes code provides time dependent high-fidelity infrared (IR) simulations of airborne vehicles, including theater missile and tactical aircraft applications.

Realtime-CHAMP 2.1.6
Real-time Composite Hardbody and Missile Plumes (RTC) Code

Platforms: UNIX, PC (cygwin)

The Real Time CHAMP code provides for sensor-in-the-loop real time (sensor frame rate) high-fidelity infrared (IR) simulations of airborne vehicles, including theater missile and tactical aircraft applications.

CHARM 2.3
Composite High Altitude Radiation Model (CHARM)

Platforms: UNIX, source included

The Composite High Altitude Radiation Model (CHARM) is the JANNAF standard computer code for calculating upper-stage and postboost missile plume infrared emission. This code treats both the altitude-independent intrinsic core and the altitude-dependent atmospheric interaction components of plume signatures for liquid and solid propellant systems.

CONTAM 3.4
Plume Contamination Effects Prediction (CONTAM)

Platforms: UNIX, source included

The CONTAM computer program provides a standardized means to predict the production, transport, deposition, and effects of monopropellant, bipropellant, and solid rocket motor plume contaminants on the environment and sensitive spacecraft surfaces.

PARCS 2.1
Plume Attenuated Radar Cross Section Code (PARCS)

Platforms: PC, source included

The Plume Attenuated Radar Cross Section Code is a FORTRAN code used to calculate the coherent and incoherent radar cross section of a rocket exhaust plume. PARCS is designed to be used with a plume properties code such as SPF.

PERCORP 2006 v2.0
Performance Correlation Program (PERCORP)

Platforms: PC, source included

The Performance Correlation Program (PERCORP) code uses known engine performance to estimate mixing and vaporization efficiencies in liquid rocket engines and provide a simple method of predicting nozzle exit-plane flow constituents and properties.

SIG v1.0
Surface Intersecting Grain (SIG)

Platforms: UNIX, source included

The Surface Intersecting Grain (SIG) computer program computes the regression of arbitrary 3D propellant grains in solid rocket motors. The code uses a finite element mesh to describe the propellant grain. The burn rate variation within the grain due to casting effects, strain level, and propellant variation can be input in 3D table form. The grain regression algorithm is a direct physical simulation of the burning process and follows burning surface elements.

SOCRATES-P 2013
Spacecraft/Orbiter Contamination Representation Accounting for Transiently Emitted Species (SOCRATES-P)

Platforms: UNIX, source included

The Spacecraft/Orbiter Contamination Representation Accounting for Transiently Emitted Species (SOCRATES) model uses the direct simulation Monte Carlo method to calculate the flowfield surrounding a spacecraft. The SOCRATES code stresses the interaction of a spacecraft’s thruster exhaust with the atmosphere. It can calculate densities, reaction rates, and radiative emission rates for these flows, including unsteady as well as steady state results.

SPF-III V5.0
Standard Plume Flowfield (SPF-III)

Platforms: UNIX, PC, source included

The Standard Plume Flowfield (SPF-III) is a JANNAF standard computer code used for predicting the gas dynamic structure of single-phase and two-phase low altitude (< 70 km) rocket exhaust plumes. SPF is used to predict plume signatures and plume/vehicle interaction phenomena, and incorporate the effects of flow over the missile body and in the base separated region.

SPIRITS AC2r2 v3 w/QF4
Spectral and In-Band Radiometric Imaging of Targets Scenes (SPIRITS)

Aircraft-2 (AC2r1) Platforms: Unix, PC(cygwin), source included

The Spectral and In-Band Radiometric Imaging of Targets Scenes (SPIRITS) Aircraft-1 code is an integrated system of computer programs designed to predict IR/UV/visible spectral and spatial data of aircraft (only IR data delivered). In addition to the SPIRITS code several aircraft target modules are also available.

SPP v7.0
Solid Propellant Rocket Motor Performance Prediction Computer Program (SPP 7.0)

Platforms: UNIX, source included

The Solid Propellant Rocket Motor Performance Prediction Computer Program (SPP), Version 7.0, predicts the average delivered performance, mass flow, pressure, thrust, and impulse as functions of time of solid rocket motors. The goal of the SPP is to predict solid rocket motor delivered specific impulse within +0.5%, and thrust and total impulse within +3%.

SPURC 3.0
Standard Plume Ultraviolet Radiation (SPURC)

Platforms: UNIX, PC, source included

The Standard Plume Ultraviolet Radiation (SPURC) is the successor to the Standard Infrared Radiation Model (SIRRM III) and is capable of predicting the UV-LWIR emissions from low altitude plumes.

TDK 93
Two Dimensional Kinetic (TDK - 93)

Platforms: UNIX, source included

The Two Dimensional Kinetic (TDK) code, March 1993 version, is a FORTRAN IV program used as a primary tool in applying the JANNAF liquid rocket thrust chamber performance prediction methodology. The TDK computer program includes a 2D nonequilibrium nozzle performance calculation with a boundary layer.

VIPER 2.2
Viscous Interaction Performance Evaluation Routine (VIPER)

Platforms: UNIX, source included

The parabolized Navier-Stokes Viscous Interaction Performance Evaluation Routine (VIPER) code, Version 2.2, calculates internal two-phase flows with turbulent and nonequilibrium reacting gases. The code is intended to improve the understanding and computational predictive capabilities for boundary layers in rocket nozzles with very high area ratios.