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The Run-time system employed by both Charm++ and AMPI has two primary features that are used by CSAR's software: load-balancing, which helps improve performance by keeping work distributed evenly across all processors, and checkpointing, which allows a lengthy computation to be saved and restarted without having to start over.
Characteristic velocity or , or C-star is a measure of the combustion performance of a rocket engine independent of nozzle performance, and is used to compare different propellants and propulsion systems. c* should not be confused with c, which is the effective exhaust velocity related to the specific impulse by: =. Specific impulse and ...
Development of REDTOP™ (Rocket Engine Design Tool for Optimal Performance) software allowing customers to experiment with factors that impact thrust, Isp, turbine speed, power balance, cost and other outputs while they design their own engine. Development of Manta™, software for high-speed propulsion for a supersonic combustion ramjet ...
The data gathered in such tests may be used to form a unique (rocket- and engine-specific) set of criteria as part of the go/no-go decision tree in the launch software that is used on launch day. Some static fire tests have fired the engines for twelve [ 4 ] and even twenty seconds, [ 5 ] although shorter firings are more typical.
Engine Origin Designer Vehicle Status Use Propellant Power cycle Specific impulse (s) [a] Thrust (N) [a] Chamber pressure (bar) Mass (kg) Thrust: weight ratio [b] Oxidiser: fuel ratio
The specific impulse of a rocket can be defined in terms of thrust per unit mass flow of propellant. This is an equally valid (and in some ways somewhat simpler) way of defining the effectiveness of a rocket propellant. For a rocket, the specific impulse defined in this way is simply the effective exhaust velocity relative to the rocket, v e ...
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Hybrid rocket fuel regression refers to the process by which the fuel grain of a hybrid-propellant rocket is converted from a solid to a gas that is combusted. It encompasses the regression rate, the distance that the fuel surface recedes over a given time, as well as the burn area, the surface area that is being eroded at a given moment.
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