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  2. Template:Engine thrust to weight table - Wikipedia

    en.wikipedia.org/wiki/Template:Engine_thrust_to...

    Template: Engine thrust to weight table. ... Print/export Download as PDF ... Merlin 1D rocket engine, full-thrust version 467 1,030 825 185,000

  3. Model rocket motor classification - Wikipedia

    en.wikipedia.org/wiki/Model_rocket_motor...

    The designation for a specific motor looks like C6-3.In this example, the letter (C) represents the total impulse range of the motor, the number (6) before the dash represents the average thrust in newtons, and the number (3) after the dash represents the delay in seconds from propelling charge burnout to the firing of the ejection charge (a gas generator composition, usually black powder ...

  4. File:Rocket thrust.svg - Wikipedia

    en.wikipedia.org/wiki/File:Rocket_thrust.svg

    The following other wikis use this file: Usage on af.wikipedia.org Straalmotor; Usage on ast.wikipedia.org Motor cohete; Usage on ca.wikipedia.org

  5. File:RocketThrust.svg - Wikipedia

    en.wikipedia.org/wiki/File:RocketThrust.svg

    Endorse this file for transfer by adding |human=<your username> to this Template. If this file is freely licensed, but otherwise unsuitable for Commons (e.g. out of Commons' scope , still copyrighted in the US), then replace this Template with {{ Do not move to Commons |reason=<Why it can't be moved>}}

  6. Thrust curve - Wikipedia

    en.wikipedia.org/wiki/Thrust_curve

    A thrust curve for a model rocket. A thrust curve, sometimes known as a "performance curve" or "thrust profile" is a graph of the thrust of an engine or motor, (usually a rocket) with respect to time. [1] [2] Most engines do not produce linear thrust (thrust which increases at a constant rate with time).

  7. Template:Rocket specs - Wikipedia

    en.wikipedia.org/wiki/Template:Rocket_specs

    Main page; Contents; Current events; Random article; About Wikipedia; Contact us; Pages for logged out editors learn more

  8. Aerojet LR87 - Wikipedia

    en.wikipedia.org/wiki/Aerojet_LR87

    The LR87 was an American liquid-propellant rocket engine used on the first stages of Titan intercontinental ballistic missiles and launch vehicles. [1] Composed of twin motors with separate combustion chambers and turbopump machinery, [2] it is considered a single unit and was never flown as a single combustion chamber engine or designed for this.

  9. Template:Thrust engine efficiency - Wikipedia

    en.wikipedia.org/wiki/Template:Thrust_engine...

    Rocket engines in vacuum; Model Type First run Application TSFC I sp (by weight) I sp (by mass) lb/lbf·h g/kN·s s m/s Avio P80: solid fuel: 2006: Vega stage 1 13 360 280 2700 Avio Zefiro 23: solid fuel: 2006: Vega stage 2 12.52 354.7 287.5 2819 Avio Zefiro 9A: solid fuel: 2008: Vega stage 3 12.20 345.4 295.2 2895 Merlin 1D: liquid fuel: 2013 ...