Numerical and experimental investigation on hypersonic inward turning inlets with basic flowfiled using arc tangent curve law of pressure rise

Xiang-jun, Nan; Kun-yuan, Zhang

doi:10.2514/6.2011-2270

Cited by 11 publications

(8 citation statements)

References 6 publications

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“…Nan et al adopted the inlet design method described Taylor and Van Wie 7 to generate an inlet with shape transition on the basis of an axisymmetric flow field with inverse tangent pressure rise. 8 The mathematical lofting method attempts to acquire a satisfactory inlet flow field by coupling with streamline-tracing. However, the lofting of two families of streamlines does not involve any aerodynamic principles, and thus the resultant inlet flow cannot well maintain the characteristics of the parent flow field.…”

Section: Stream-tracing-based Mathematical Lofting Methodmentioning

confidence: 99%

Design methodology for shape transition inlets based on constant contraction of discrete streamtubes

Xiao

Yue

et al. 2015

Proceedings of the Institution of Mechanical Engineers, Part G:

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In this paper we propose a design concept, i.e. constant contraction of discrete streamtubes, to develop a new design method for hypersonic inlets with shape transition, which enables the shape transition inlet to have high compression efficiency while keeping flow uniformity as much as possible. The method first divides the 3D flow field of the inlet into several groups of discrete streamtubes with constant contraction ratio. The axisymmetric flow within each stream tube is then optimized via computational fluid dynamics to have high compression efficiency, and these discrete streamtube groups are finally assembled together by matching their shock wave reflection positions to form a 3D inlet flow field with weak crossflow. This method can be used for the design of shape transition inlets with specified entrance/exit sections. To validate the present methodology, we design a rectangular-to-circular inlet with a design point of Ma 6 and a takeover point of Ma 4, and examine numerically the flow structure and the inlet performances.

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Section: Stream-tracing-based Mathematical Lofting Methodmentioning

confidence: 99%

Design methodology for shape transition inlets based on constant contraction of discrete streamtubes

Xiao

Yue

et al. 2015

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…[8][9][10][11] Then based on the in-depth analysis of the characteristics and flow equation of the curved shock compression flow field, the inverse design method with controllable aerodynamic parameters (pressure, Mach number, etc.) 12 along the compression surface airstream, controllable outflow parameters 13 or controllable shock wave shape 14 is proposed. The method of constructing curved surface through coordinate transformation of conventional isentropic compression surface 15 is also studied.…”

Section: Curved Shock Compression Systemmentioning

confidence: 99%

“…12 The basic idea is to make use of traditional method of characteristics, while the boundary condition of wall coordinate is replaced by aerodynamic parameters (such as pressure, velocity, etc.) to solve the equations so as to obtain the wall coordinate.…”

Section: Experimental Investigation Of Curved Shock Compression Witmentioning

confidence: 99%

Research Progress of Hypersonic Inlet Inverse Design Based on Curved Shock Compression System

Zhang¹

2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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This paper gives a summary on curved shock compression research in the last decade. The new concept of curved shock compression system is proposed, in which specially designed 2D or 3D curved compression surface is applied. The leading shock wave would be curved due to its interaction with isentropic compression waves near the compression surface, and free stream is compressed by the curved shock wave together with the isentropic waves. Based on this concept, methods of: inverse designing supersonic internal flow path according to assigned outflow parameters, inverse designing compression surface according to pressure distribution or Mach number distribution along the surface, and inverse designing surface according to shock wave shape are established. The curved shock compression has a good comprehensive performance as shown in the investigation, and represents a brand-new approach for the design of hypersonic propulsion compression system.

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“…13 Recently, Xiangjun Nan made numerical and experimental investigation on hypersonic inward turning inlets with controlled pressure gradient. 14,15 All the design methods of inlets are similar. First, design basic flowfield by specific method, then generate the inviscid configuration of inlets using streamtracing or section gradient techniques and make viscous correction.…”

Section: Introductionmentioning

confidence: 98%

Design of hypersonic inward turning inlets with controllable Mach number distribution

Li¹,

Nan²

2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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A method has been devised for the design of hypersonic inward turning inlets. On condition that the Mach number distribution along the surface of basic flowfield had been given, this method applied the rotational method of characteristics to design axisymmetric flowfield and streamtracing techniques to generate an invisid configuration, and then designed final inlets with viscous correction. Five typical kinds of basic flowfields designed under same constraints had been investigated. Complete design procedure was described based on the law of arc tangent Mach number distribution, and the characteristics of a hypersonic inward turning inlet with circular shape entrance were studied through number simulation. The results indicate that, there is a biggish diversity between Mach numerical distributions and its corresponding law of pressure rise; Busemann basic flowfield is very similar to constant Mach number gradient distribution; the basic flowfield with arc tangent Mach number distribution has the best general performance; the Mach number distribution on streamlines of the surface of inlets dovetails well with basic flowfield; this kind of inlet has a good performance and its general performance is roughly equivalent to an inlet with controlled pressure gradient at design point. Nomenclature CRI= internal contraction ratio of inlet CRT = total contraction ratio of inlet Ma = Mach number Ma r = Mach number on the wall behind leading shock wave a, b, c = coefficient of arc tangent curve c 1 , c 2 , c 3 = coefficient of curve p = static pressure R = radius x = coordinate direction = compression angle of leading edge = total pressure recovery coefficient Subscripts 0 = free stream c = center body e = exit plane i = intake plane th = throat plane

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Numerical and experimental investigation on hypersonic inward turning inlets with basic flowfiled using arc tangent curve law of pressure rise

Cited by 11 publications

References 6 publications

Design methodology for shape transition inlets based on constant contraction of discrete streamtubes

Design methodology for shape transition inlets based on constant contraction of discrete streamtubes

Research Progress of Hypersonic Inlet Inverse Design Based on Curved Shock Compression System

Design of hypersonic inward turning inlets with controllable Mach number distribution

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