S1904-2-2 ラバールノズルでの対流熱伝達を利用した推力・比推力の向上(大気突入・減速技術(2))

概要

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The one-dimensional analysis has been performed using the analysis program for the flow of the propellant of Laval nozzles. The propellant is nitrogen. Two kinds of nozzle that has a throat diameter of 0.5 mm and 1 mm are assumed. Heat flow to the propellant by convective heat transfer in the supersonic region is increased by elongating of the divergent section of the nozzle. The ratio of the exhaust velocity with the heat transfer in the nozzle to the exhaust velocity without the heat transfer is not affected by the throat diameter, inlet pressure, and temperature difference between the nozzle wall and the propellant. In the case that the throat diameter of 0.5 mm, inlet pressure of 1 MPa, temperature difference of 300 K and length of the divergent section of 200 mm, the ratio of the exhaust velocity becomes 1.05.
社団法人日本機械学会の論文
2009-09-12