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The maximum temperature of a droplet during the combustion process is more than 1100 K.
It is one of the environmental pollutants generated by internal-combustion engines, resulting from the reaction of nitrogen and oxygen in the air during the combustion process.
At last, the heat loss during the combustion process was calculated by the difference between experimental and adiabatic explosion pressure.
Cd, Pb, and Zn occurred during the combustion process in the form of elementary substances and their oxides.
Furthermore combustion pressures and heat radiation from the sonic jet flame during the combustion process were measured.
The model allows the determination of the state of unburned gas and combustion products during the combustion process.
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The resulting thermochemical trajectories are used to examine the evolution of thermodynamic quantities and chemical composition, as well as measure fluid parcel residence times and path lengths during different phases of the combustion process.
A single irreversible chemical reaction for a C2H4+3O2+4N2 mixture is used to represent the combustion process during the interactions.
The combustion process occurs during the expansion stroke, in a quasi-isobaric process.
According to [19], the resulting composition of biomass affects its combustion characteristics as the total overall mass of the fuel decreases during the volatile combustion phase of the combustion process, as the hydrogen to carbon ratio of the fuel increases and, to a lesser extent, as the oxygen to carbon ratio increases.
The combustion process and rocket operation during mode transition were investigated by direct-connect tests.
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