Streamline tracing: Technique for designing hypersonic vehicles
Streamline tracing: Technique for designing hypersonic vehicles
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DOI：
10.2514/2.5591
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发表时间：
2000-05-01
影响因子：
1.9
通讯作者：
Kothari, AP
中科院分区：
文献类型：
--
作者：
Billig, FS;Kothari, AP
本文介绍了高超声速吸气式发动机流线型平面和轴对称进气道的一大类设计方法。本文通过讨论Busemann进气道流场的流线跟踪来介绍这一问题，Busemann进气道流场的流线跟踪是超音速燃烧冲压喷气导弹（SCRAM）发动机设计的一个步骤。简要介绍了SCRAM的试验结果，以证明流线跟踪技术的有效性。广义模型涵盖了从外旋等熵尖到内旋进气道的整个流场范围。引入径向偏差参数作为描述设计族成员的变量。示出了各种进气道形状和飞行器构型以演示设计过程。论证了基于内转向流场流线迹线的发动机设计的可行性。
The methodology for creating a large family of designs of streamline traced planar and axisymmetric inlets for hypersonic airbreathing engines is presented. The subject is introduced by a discussion of streamline tracing of Busemann inlet flowfields, which was the procedure that was used to design the Supersonic Combustion Ramjet Missile (SCRAM) engine. A brief synopsis of test results of SCRAM is presented to demonstrate the efficacy of the streamline tracing technique. The generalized model covers the complete range of flow fields from outward-turning isentropic spikes to inward turning inlets. The radial deviation parameter is introduced as the variable to describe the members of the design family. A variety of inlet shapes and vehicle configurations are shown to demonstrate the design procedure. Arguments are made to support the viability of engine designs based of streamline traces of inward-turning flowfields.