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The small particles in the expanding exhaust plume or "cloud" diffract sunlight and produce the rose, blue, green and orange colors—much like a dispersive prism can be used to break light up into its constituent spectral colors (the colors of the rainbow) – thereby making the twilight phenomenon all the more spectacular.
The main flame deflector in the flame trench at Launch Complex 39B at NASA's Kennedy Space Center in Florida. It deflects the plume exhaust from NASA's Space Launch System rocket during launch. It features a new "steel plated" design and incorporates water pipes for sound suppression. [1]
CFD is often undertaken for rocket plumes, where condensed phase constituents can be present in addition to gaseous constituents. These types of simulations can become quite complex, including afterburning and thermal radiation , and (for example) ballistic missile launches are often detected by sensing hot rocket plumes.
Shock diamonds are the bright areas seen in the exhaust of this statically mounted Pratt & Whitney J58 engine on full afterburner.. Shock diamonds (also known as Mach diamonds or thrust diamonds, and less commonly Mach disks) are a formation of standing wave patterns that appear in the supersonic exhaust plume of an aerospace propulsion system, such as a supersonic jet engine, rocket, ramjet ...
A space jellyfish (also jellyfish UFO or rocket jellyfish) is a rocket launch-related phenomenon caused by sunlight reflecting off the high-altitude rocket plume gases emitted by a launching rocket during morning or evening twilight. The observer is in darkness, while the exhaust plumes at high altitudes are still in direct sunlight.
The rocket's exhaust plume was observed and reported to news organizations in the United States from New Jersey to Massachusetts. [38] A 2018 experiment briefly created noctilucent clouds over Alaska, allowing ground-based measurements and experiments aimed at verifying computer simulations of the phenomenon.
As an example calculation using the above equation, assume that the propellant combustion gases are: at an absolute pressure entering the nozzle of p = 7.0 MPa and exit the rocket exhaust at an absolute pressure of p e = 0.1 MPa; at an absolute temperature of T = 3500 K; with an isentropic expansion factor of γ = 1.22 and a molar mass of M ...
Employment on a single-stage-to-orbit (SSTO) rocket would use an E-D nozzle's altitude compensating abilities fully, allowing for a substantial increase in payload. Reaction Engines, Airborne Engineering and the University of Bristol are currently involved in the STERN (Static Test Expansion deflection Rocket Nozzle) project [ 9 ] to assess the ...