理论设计和弹进的计算流体动力学分析(IJISA-V3-N5-8)

Theoretical Design and Computational Fluid Dynamic Analysis of Projectile Intake

I.J. Intelligent Systems and Applications, 2011, 5, 56-63

Published Online August 2011 in MECS (doc.docsou.com)

Theoretical Design and Computational Fluid Dynamic Analysis of Projectile Intake

Wei Wang

Science and Technology on Combustion, Internal Flow and Thermo-Structure Laboratory,

Northwestern Polytechnical University, Xi’an, China

midule@mail.nwpu.edu.cn

Likun Cui and Zhuo Li

College of science, Inner Mongolia University of Technology, Hohhot, China

lekuncui@sina.com and li_zhuo@263.net

Abstract—With the development of the science and desires. The previous studies by some institutions at technology, the more requirements such as cost effective, home and abroad revealed the potential to provide high specific impulse in wide operation rang, becomes efficient and flexible airflow which the combustion stricter and multiplicity. However, the existing supersonic requires [1-2].This interest in the supersonic projectile inlet can no longer adjust to all the new projectiles. In this

inlet encouraged our research team to proceed with paper, based on the basic characteristic of inlet and

considering the design requirements, the two-dimensional design and verification of a new one.

This paper’s study is carried out as a part of the wide supersonic projectile inlet was designed and verified by

numerical simulation under different operating conditions research on solid rocket ramjet extended range projectile. such as attack angle, altitude, and so on. The results are So in following sections, a two-dimensional supersonic shown that: 1) The design process is successful, but the projectile inlet, which parameter selection must be carried working conditions should be limited to the small angle of out keeping in mind the number of stages and the overall attack; 2) The total pressure recovery coefficient is projectile diameter, was designed and verified by increasing as the Ma number increases, and then is numerical simulation under different operating conditions gradually decreased after the point of Mach number is

based on the basic characteristic of the inlet and equal to 0.5; 3) The existence of attack angle reduces values

of total pressure recovery. And moreover, the shock wave considering the design requirement.

which occurs at the anterior point is gradually deviating from projectile body direction with the increase of attack angle; 4). The variance ratio in the outlet has the acute changed with increasing of altitudes clearly, but its corresponding values degrade sharply in the entrance.

Index Terms—supersonic air inlet, two-dimension, ramjet projectile, numerical simulation, influence factors

II. INLET DESIGN

It is well known that the effects of each factor such as flight altitude, attack angle, airflow, inlet Mach number of the combustion chamber, and so on, have been discussed respectively in many books and articles [3-5], but there is still some disagreement over important issues. In this section, we are concerned with design of supersonic flow in projectile intake base on classical

I. INTRODUCTION theories and practice experiences. The majority work is

With the development of the science and technology, determined of the design method in this period. At the the more requirements such as cost effective, high end of the process, the Oswatisch design method is specific impulse in wide operation rang, becomes stricter selected, and moreover, several design requirements, and multiplicity. However, the existing supersonic inlet, which list in Table I, have now been built to verify such a which is the entrance channel of the solid rocket ramjet flow system under the conditions of considering various engine and plays a crucial role in assisted range desires [6]. performance, can no longer adjust to all the new TABLE I. projectiles. Thus this situation has led renews interest in PAPERS DESIGN REQUIREMENTS the inlet design and performance validation. Researchers’

studies and experiments have confirmed the theoretical

operation and demonstrated the feasibility of the two-Mach number of incoming flow

3.50

dimensional inlet as an air supply system that meets those

Total pressure recovery coefficient Combustor inlet Mach number

Inlet flow rate Inlet number

>0.27

<0.40 >2.0 kg/s 4.00

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