Legacy JANNAF Codes | Joint Army Navy NASA Air Force

Legacy JANNAF Codes

Legacy Tools
Several JANNAF codes have been superseded by newer software and are no longer supported.  However, these legacy tools are still available provided sufficient justification is provided.  
 
CELMINT 6.05
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
The Composite Hardbody And Missile Plumes code provides time dependent, high-fidelity, infrared (IR) simulations of airborne vehicles, including theater missiles and tactical aircraft.
 
Realtime-CHAMP 2.1.6
The Real Time CHAMP code provides sensor-in-the-loop, real-time (sensor frame rate), high-fidelity IR simulations of airborne vehicles, including theater missiles and tactical aircraft.
 
CHARM 2.3
The Composite High Altitude Radiation Model (CHARM) was the previous JANNAF code for calculating upper-stage and post-boost missile plume infrared emissions.  (It has been superseded by SOCRATES-P.)  CHARM computes both the altitude-independent intrinsic core and the altitude-dependent atmospheric interactions that produce the plume signatures of liquid and solid propellant systems.
 
CONTAM 3.4
The Plume Contamination Effects Prediction Program (CONTAM) calculates the production, transport, deposition, and effects of monopropellant, bipropellant, and solid rocket motor exhaust plume contaminants on the environment and sensitive spacecraft surfaces.
 
PARCS 2.1
The Plume Attenuated Radar Cross Section (PARCS) code is used to calculate the coherent and incoherent radar cross section of a rocket exhaust plume.  It is designed to be used with an  exhaust plume flowfield code.
 
SIG v1.0
The Surface Intersecting Grain (SIG) computer program computes the regression of arbitrary 3D propellant grains in solid rocket motors.  It uses a finite element mesh to describe the propellant grain and it accounts for burn rate variation due to casting effects and strain level.  In addition, the propellant variation can be input via a 3D table.  The grain regression algorithm is a direct physical simulation of the burning process that follows burning surface elements.
 
SPF-III v5.0
The Standardized Plume Flowfield (SPF-III) code was the previous JANNAF code for predicting the flowfield structure and properties of single-phase and two-phase, low altitude (below 70 km), rocket exhaust plumes.  It accounts for the effects of flow over the missile body and in the separated base region.
 
TDK – 93
The Two Dimensional Kinetic code, March 1993 version (TDK-93), is calculates the performance of a liquid rocket exhaust nozzle with 2D non-equilibrium chemistry and a boundary layer.