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  2. Ultrasonic nozzle - Wikipedia

    en.wikipedia.org/wiki/Ultrasonic_Nozzle

    Ultrasonic spray nozzle technology has been used to create films of indium tin oxide (ITO) in the formation of transparent conductive films (TCF). [9] ITO has excellent transparency and low sheet resistance, however it is a scarce material and prone to cracking, which does not make it a good candidate for the new flexible TCFs.

  3. Nozzle - Wikipedia

    en.wikipedia.org/wiki/Nozzle

    Air-aspirating nozzles use an opening in the cone shaped nozzle to inject air into a stream of water based foam (CAFS/AFFF/FFFP) to make the concentrate "foam up". Most commonly found on foam extinguishers and foam handlines. Swirl nozzles inject the liquid in tangentially, and it spirals into the center and then exits through the central hole ...

  4. de Laval nozzle - Wikipedia

    en.wikipedia.org/wiki/De_Laval_nozzle

    The analysis of gas flow through de Laval nozzles involves a number of concepts and assumptions: For simplicity, the gas is assumed to be an ideal gas. The gas flow is isentropic (i.e., at constant entropy). As a result, the flow is reversible (frictionless and no dissipative losses), and adiabatic (i.e., no heat enters or leaves the system).

  5. K-factor (fire protection) - Wikipedia

    en.wikipedia.org/wiki/K-factor_(fire_protection)

    This page was last edited on 28 December 2024, at 14:21 (UTC).; Text is available under the Creative Commons Attribution-ShareAlike 4.0 License; additional terms may apply.

  6. Propelling nozzle - Wikipedia

    en.wikipedia.org/wiki/Propelling_nozzle

    Beyond this point the nozzle diameter becomes the biggest diameter and starts to incur increasing drag. Nozzles are thus limited to the installation size and the loss in thrust incurred is a trade off with other considerations such as lower drag, less weight. Examples are the F-16 at Mach 2.0 [21] and the XB-70 at Mach 3.0. [22]

  7. Rocket engine nozzle - Wikipedia

    en.wikipedia.org/wiki/Rocket_engine_nozzle

    The optimal size of a rocket engine nozzle is achieved when the exit pressure equals ambient (atmospheric) pressure, which decreases with increasing altitude. The reason for this is as follows: using a quasi-one-dimensional approximation of the flow, if ambient pressure is higher than the exit pressure, it decreases the net thrust produced by ...