Abstract
Free jet experiments have been conducted to evaluate the performance of a cavity-type ramjet. To prevent uncertainty of combustion parameters, a method to calculate internal thrust from cold flow parameters is brought forward. According to this analysis method, the internal thrust of the cavity-type ramjet increases linearly with the stoichiometric ratio while the specific impulse decreases squarely. The aero-propulsive balance of a conceptive missile is also examined, focusing on the effect of attack angle. Considering both efficiency and performance, an attack angle of 3∼6 degrees is recommended. And the free-jet experimental results show that the cavity-type ramjet can supply sufficient thrust for the missile under cruise conditions.
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This paper was recommended for publication in revised form by Associate Editor Oh Chae Kwon
Jianguo Tan, received B.S., M.S. and Ph.D degrees from the National University of Defense Technology, P. R. China, in 1997, 2000 and 2003, respectively. He also studied at Oxford University as a visiting scholar in 2007∼2008. He is currently an associate professor in the above-mentioned university and his main research interest lies in rocket propulsion and air-breathing propulsion
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Tan, J., Pan, Y., Liang, J. et al. A free-jet experimental study on the performance of a cavity-type ramjet. J Mech Sci Technol 25, 2951–2957 (2011). https://doi.org/10.1007/s12206-011-0814-0
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DOI: https://doi.org/10.1007/s12206-011-0814-0