### Abstract

Relevance of the research. The efficiency of fuel chemical energy conversion into mechanical motion of a supersonic aircraft is determined by energy losses due to aerodynamic drag of the aircraft and total pressure losses in the air inlet of jet engine. Therefore, ceteris paribus the aircraft with lower level of these losses will be more energy efficient. Significant increase in energy efficiency is expected from the use of axisymmetric isentropic ducted air inlets. In the framework of the non-viscous flow, a numerical method is offered for these air inlets with a contoured central body and a cylindrical shell designing. The main aim of the study. Currently there are no designing methods for axisymmetric isentropic ducted air inlets without elements projecting over a cylindrical body of the aircraft. Therefore, the aim of the study is to develop a methodology for designing such inlets. The methods used in the study. Numerical implementation of the characteristics method for isentropic flow is used. The proposed method involves the decision of two problems. In the first problem a flow line around the given focus point of characteristics which starts at a break point of central body is plotted. In the second problem the rest of the contour is calculated using the reversed flow in an annular nozzle with a cylindrical shell. Simultaneously with the decision of the second problem, the position of the shell is determined. The central body can contain angular points at the edges of the contour. If we use an intermediate flow line then the central body will be smooth. The results. The authors developed the methodology for calculating different axisymmetric supersonic air inlet contours, which geometrical characteristics are uniquely described by the original data.

Original language | English |
---|---|

Pages (from-to) | 117-124 |

Number of pages | 8 |

Journal | Bulletin of the Tomsk Polytechnic University, Geo Assets Engineering |

Volume | 326 |

Issue number | 4 |

Publication status | Published - 2015 |

### Fingerprint

### Keywords

- Ducted axisymmetric air inlet
- Energy efficiency
- Ideal perfect gas
- Isentropic flow
- Method of characteristics
- Supersonic flow

### ASJC Scopus subject areas

- Economic Geology
- Geotechnical Engineering and Engineering Geology
- Fuel Technology
- Management, Monitoring, Policy and Law
- Waste Management and Disposal
- Materials Science (miscellaneous)

### Cite this

*Bulletin of the Tomsk Polytechnic University, Geo Assets Engineering*,

*326*(4), 117-124.

**Forming of ducted axisymmetric supersonic air inlets.** / Galkin, Vladislav M.; Zvegintsev, Valery I.

Research output: Contribution to journal › Article

*Bulletin of the Tomsk Polytechnic University, Geo Assets Engineering*, vol. 326, no. 4, pp. 117-124.

}

TY - JOUR

T1 - Forming of ducted axisymmetric supersonic air inlets

AU - Galkin, Vladislav M.

AU - Zvegintsev, Valery I.

PY - 2015

Y1 - 2015

N2 - Relevance of the research. The efficiency of fuel chemical energy conversion into mechanical motion of a supersonic aircraft is determined by energy losses due to aerodynamic drag of the aircraft and total pressure losses in the air inlet of jet engine. Therefore, ceteris paribus the aircraft with lower level of these losses will be more energy efficient. Significant increase in energy efficiency is expected from the use of axisymmetric isentropic ducted air inlets. In the framework of the non-viscous flow, a numerical method is offered for these air inlets with a contoured central body and a cylindrical shell designing. The main aim of the study. Currently there are no designing methods for axisymmetric isentropic ducted air inlets without elements projecting over a cylindrical body of the aircraft. Therefore, the aim of the study is to develop a methodology for designing such inlets. The methods used in the study. Numerical implementation of the characteristics method for isentropic flow is used. The proposed method involves the decision of two problems. In the first problem a flow line around the given focus point of characteristics which starts at a break point of central body is plotted. In the second problem the rest of the contour is calculated using the reversed flow in an annular nozzle with a cylindrical shell. Simultaneously with the decision of the second problem, the position of the shell is determined. The central body can contain angular points at the edges of the contour. If we use an intermediate flow line then the central body will be smooth. The results. The authors developed the methodology for calculating different axisymmetric supersonic air inlet contours, which geometrical characteristics are uniquely described by the original data.

AB - Relevance of the research. The efficiency of fuel chemical energy conversion into mechanical motion of a supersonic aircraft is determined by energy losses due to aerodynamic drag of the aircraft and total pressure losses in the air inlet of jet engine. Therefore, ceteris paribus the aircraft with lower level of these losses will be more energy efficient. Significant increase in energy efficiency is expected from the use of axisymmetric isentropic ducted air inlets. In the framework of the non-viscous flow, a numerical method is offered for these air inlets with a contoured central body and a cylindrical shell designing. The main aim of the study. Currently there are no designing methods for axisymmetric isentropic ducted air inlets without elements projecting over a cylindrical body of the aircraft. Therefore, the aim of the study is to develop a methodology for designing such inlets. The methods used in the study. Numerical implementation of the characteristics method for isentropic flow is used. The proposed method involves the decision of two problems. In the first problem a flow line around the given focus point of characteristics which starts at a break point of central body is plotted. In the second problem the rest of the contour is calculated using the reversed flow in an annular nozzle with a cylindrical shell. Simultaneously with the decision of the second problem, the position of the shell is determined. The central body can contain angular points at the edges of the contour. If we use an intermediate flow line then the central body will be smooth. The results. The authors developed the methodology for calculating different axisymmetric supersonic air inlet contours, which geometrical characteristics are uniquely described by the original data.

KW - Ducted axisymmetric air inlet

KW - Energy efficiency

KW - Ideal perfect gas

KW - Isentropic flow

KW - Method of characteristics

KW - Supersonic flow

UR - http://www.scopus.com/inward/record.url?scp=85006153291&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=85006153291&partnerID=8YFLogxK

M3 - Article

AN - SCOPUS:85006153291

VL - 326

SP - 117

EP - 124

JO - Bulletin of the Tomsk Polytechnic University, Geo Assets Engineering

JF - Bulletin of the Tomsk Polytechnic University, Geo Assets Engineering

SN - 2500-1019

IS - 4

ER -