Abstract
Full-scale and computational experiments were used to investigate the flows in the jet thrust unit with annular nozzle and deflector in the form of a spherical segment. The used working gas was the combustion products of air mixtures with acetylene, gas-phase aviation kerosene, and natural gas. Experimental studies were carried out in a hot-shot wind tunnel in the range of stagnation pressure from 0.48 to 2.05 MPa. The calculations for the cases of combustion products outflow in terrestrial and high altitude conditions were performed with the original computer program that used the Euler and Navier-Stokes systems supplemented by equations of chemical kinetics. It was found that the thrust of the jet module with an annular nozzle at high altitude almost twice exceeds the sound nozzle thrust, but is lesser (about 25 %) than the thrust of the ideal calculated Laval nozzle; the difference therewith decreases markedly with the decrease of flight altitude and stagnation pressure.
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The work was financially supported by the Russian Foundation for Basic Research (Grants No. 11-01-00068-a and No. 12-01-90416-Ucr_a), and by the President of the Russian Federation (Grant for supporting leading scientific schools of RF, No. NSh.-5911.2012.1), and programs of RAS Presidium.
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Levin, V.A., Afonina, N.E., Gromov, V.G. et al. Investigating an annular nozzle on combustion products of hydrocarbon fuels. Thermophys. Aeromech. 20, 265–272 (2013). https://doi.org/10.1134/S0869864313030013
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DOI: https://doi.org/10.1134/S0869864313030013