Investigation on a streamtraced hypersonic Busemann inlet

Sun, Baojiang; Zhang, K-Y; Wang, C-P; Wu, Xiaosong

doi:10.1243/09544100jaero545

Cited by 10 publications

(5 citation statements)

References 19 publications

(20 reference statements)

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“…Equation (6) shows that if the pressure ratios p 30 and total pressure recovery coefficients s 30 of any two streamtubes are equal, their contraction ratios are identical too. The property that any streamtube in a flow field has the same contraction ratio is defined in this paper as ''constant contraction.''…”

Section: Constant Contraction and Flow Uniformitymentioning

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: Constant Contraction and Flow Uniformitymentioning

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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“…) After Fourier transformation, Eq. 3 is changed into the spectral density matrix of (5) where S F(t) (ω) is the spectral density matrix of F(t) in Eq. 1,…”

Section: The Description Of Random Excitationmentioning

confidence: 99%

“…Experiment equipment is the ES-50000 electric vibration table and the acceleration sensor is installed the position of measurement point. The experiment parameter is shown in Table 1 [5,6]. The real object of this mechanism is shown in Fig.…”

Section: Random Vibration Experimentsmentioning

confidence: 99%

Dynamic Analysis of a Calibration Mechanism

Sun

Chen

Zhang

2010

AMM

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In order to verify the reliability of a calibration mechanism including a motion component used in the satellite, the dynamic analysis for this mechanism is conducted with modal coordinate reduction method. Firstly, FEM software ABAQUS is employed to calculate the eigenfrequency and mode shapes of this mechanism. Then, the transfer function at some key points can be acquired by coordinate transformation from its original format in modal coordinate. Finally, the power spectral density at the key points are obtained and compared with the results of random vibration experiments to prove the dynamics analytical validity.

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“…1 Since the sixties of last century, domestic and foreign researchers have done lots of work on hypersonic inward turning inlets, particularly the Busemann inlets. [2][3][4] Studies have shown that this type of inlet has advantages of higher capture flow and compression efficiency, smaller infiltration area, wider adaptability etc.…”

Section: Introductionmentioning

confidence: 99%

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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Investigation on a streamtraced hypersonic Busemann inlet

Cited by 10 publications

References 19 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

Dynamic Analysis of a Calibration Mechanism

Design of hypersonic inward turning inlets with controllable Mach number distribution

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