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Soltani, M.R., Sepahi Yoinsi, J., Farajpoor Khanaposhtani, V.. (1394). NUMERICAL INVESTIGATION OF THE UNSTART SUPPRESSION IN A SUPERSONIC AIR INTAKE. , 39(M2), 413-426. doi: 10.22099/ijstm.2015.3249
M.R. Soltani; J. Sepahi Yoinsi; V. Farajpoor Khanaposhtani. "NUMERICAL INVESTIGATION OF THE UNSTART SUPPRESSION IN A SUPERSONIC AIR INTAKE". , 39, M2, 1394, 413-426. doi: 10.22099/ijstm.2015.3249
Soltani, M.R., Sepahi Yoinsi, J., Farajpoor Khanaposhtani, V.. (1394). 'NUMERICAL INVESTIGATION OF THE UNSTART SUPPRESSION IN A SUPERSONIC AIR INTAKE', , 39(M2), pp. 413-426. doi: 10.22099/ijstm.2015.3249
Soltani, M.R., Sepahi Yoinsi, J., Farajpoor Khanaposhtani, V.. NUMERICAL INVESTIGATION OF THE UNSTART SUPPRESSION IN A SUPERSONIC AIR INTAKE. , 1394; 39(M2): 413-426. doi: 10.22099/ijstm.2015.3249

NUMERICAL INVESTIGATION OF THE UNSTART SUPPRESSION IN A SUPERSONIC AIR INTAKE

Iranian Journal of Science and Technology Transactions of Mechanical Engineering
مقاله 10، دوره 39، M2، دی 2015، صفحه 413-426    اصل مقاله (931.61 K)
نوع مقاله: Research Paper
شناسه دیجیتال (DOI): 10.22099/ijstm.2015.3249
نویسندگان
M.R. Soltani* 1؛ J. Sepahi Yoinsi2؛ V. Farajpoor Khanaposhtani3
1Dept. of Aerospace Engineering, Sharif University of Technology, Tehran, I. R. of Iran
2Dept. of Aerospace Engineering, Sharif University of Technology, Tehran, I. R. of Iran and Mesbah Research Institute, Tehran, I. R. of Iran
3Mesbah Research Institute, Tehran, I. R. of Iran
چکیده
The starting behavior of a supersonic axisymmetric mixed compression air intake was numerically investigated. The code solves Reynolds-averaged Navier–Stokes equations using an explicit finite volume method in a structured grid by the Roe flux difference splitting scheme. Further, it uses the Baldwin–Lomax algebraic model to compute the turbulent viscosity coefficient. The correct method of surveying the intake starting problem and effects of several geometrical parameters such as: intake throat area, cowl lip roundness and spike surface curvature upstream of the throat on the starting and performance of the intake were studied. Results showed that correct combinations of the mentioned parameters can suppress the intake unstart problem and in addition can prevent the reduction of the intake efficiency.
کلیدواژه‌ها
Supersonic air intake؛ starting problem؛ throat area؛ cowl lip roundness؛ spike surface curvature؛ intake efficiency
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