The Plume Impingement Program (PLIMP) is a computer code used to predict impact pressures, forces, moments, heating rates, and contamination on surfaces due to direct impingement flowfields. Typically, it has been used to analyze the effects of rocket exhaust plumes on nearby structures from ground level to the vacuum of space. The program normally uses flowfields generated by the MOC, RAMP2, SPF/2, or SFPGEN computer programs. It is capable of analyzing gaseous and gas/particle flows. A number of simple subshapes are available to model the surfaces of any structure. The original PLIMP program has been modified many times of the last 20 years. The theoretical bases for the referenced major changes, and additional undocumented changes and en...
Results are presented for an experimental space shuttle stage separation plume impingement program c...
Computer program determines the radiant flux to the base region of a real gas system with an axisymm...
Technology for simulating plumes in wind tunnel tests was not adequate to provide the required confi...
The objective of this contract was to continue development of a vacuum plume impingement evaluator t...
Plume Impingement modeling is required whenever an object immersed in a rocket exhaust plume must su...
A summary is presented of the various documents that discuss and describe the computer programs and ...
The Orion Crew Exploration Vehicle Service Module Reaction Control System engine plume impingement w...
The flowfield codes that have been developed to predict rocket motor plumes at high altitude were us...
The Orion Crew Exploration Vehicle Service Module Reaction Control System engine plume impingement w...
Computer program manual to analyze loads and heating on bodies subject to rocket exhaust impingemen
Engineering methods and computer programs for predicting convective heat flux and pressure in flow r...
Computer programs and engineering methods for calculating heating rates and forces in jet plume impi...
A users manual for the RAMP2 computer code is provided. The RAMP2 code can be used to model the domi...
All of the elements used in the Reacting and Multi-Phase (RAMP2) computer code are described in deta...
Solar thermal upper stage propulsion systems currently under development utilize small low chamber p...
Results are presented for an experimental space shuttle stage separation plume impingement program c...
Computer program determines the radiant flux to the base region of a real gas system with an axisymm...
Technology for simulating plumes in wind tunnel tests was not adequate to provide the required confi...
The objective of this contract was to continue development of a vacuum plume impingement evaluator t...
Plume Impingement modeling is required whenever an object immersed in a rocket exhaust plume must su...
A summary is presented of the various documents that discuss and describe the computer programs and ...
The Orion Crew Exploration Vehicle Service Module Reaction Control System engine plume impingement w...
The flowfield codes that have been developed to predict rocket motor plumes at high altitude were us...
The Orion Crew Exploration Vehicle Service Module Reaction Control System engine plume impingement w...
Computer program manual to analyze loads and heating on bodies subject to rocket exhaust impingemen
Engineering methods and computer programs for predicting convective heat flux and pressure in flow r...
Computer programs and engineering methods for calculating heating rates and forces in jet plume impi...
A users manual for the RAMP2 computer code is provided. The RAMP2 code can be used to model the domi...
All of the elements used in the Reacting and Multi-Phase (RAMP2) computer code are described in deta...
Solar thermal upper stage propulsion systems currently under development utilize small low chamber p...
Results are presented for an experimental space shuttle stage separation plume impingement program c...
Computer program determines the radiant flux to the base region of a real gas system with an axisymm...
Technology for simulating plumes in wind tunnel tests was not adequate to provide the required confi...