Operation pattern classification of hypersonic inlets

Chang, Juntao; Yu, Daren; Bao, Wen; Fan, Yi

doi:10.1016/j.actaastro.2009.02.011

Cited by 33 publications

(13 citation statements)

References 28 publications

(46 reference statements)

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“…For the preparation, see: Cushman & Kanamathareddy (1990); Mé ric et al (1993). For the structures of similar compounds, see: Lu et al (2011); Zhang et al (2009); Liu et al (2009). For graph-set analysis, see Etter et al (1990).…”

Section: Related Literaturementioning

confidence: 99%

Dimethyl 5,5′-methylenebis(2-hydroxybenzoate)

2012

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In the title compound, C17H16O6, the two methyl salicylate moieties are related by crystallographic twofold rotational symmetry with the two benzene rings close to being perpendicular [inter-ring dihedral angle = 86.6 (8)°]. Intramolecular phenolic O—H⋯O hydrogen bonds with carboxyl O-atom acceptors are present, with these groups also involved in centrosymmetric cyclic intermolecular O—H⋯O hydrogen-bonding associations [graph set R 2 2(4)], giving infinite chains extending across (101).

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Section: Related Literaturementioning

confidence: 99%

Dimethyl 5,5′-methylenebis(2-hydroxybenzoate)

2012

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“…Chang (9,10) investigated hypersonic inlet with pulse periodic energy addition. Yu (11)(12)(13) discussed the feature selection, pattern classification of hypersonic inlet start/unstart based on 'numerical experimental' data, and Sang (14) and Owens (15) discussed supersonic inlet design and active flow control respectively. Chang (16,17) investigated unstart boundary and margin control of a hypersonic inlet, and Cui (18,19) discussed the catastrophe, hysteresis and bifurcation of hypersonic inlet start/unstart.…”

Section: Effect Of Boundary Layer Bleeding On Unstart Oscillatory Flomentioning

confidence: 99%

Effects of boundary-layer bleeding on unstart oscillatory flow of hypersonic inlets

Fan¹,

Chang²,

Bao³

et al. 2010

Aeronaut. j.

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The unsteady flowfield of a series of mixed-compression hypersonic inlets with different bleeding rates were numerically simulated. Firstly unstart oscillatory flow of hypersonic inlets caused by downstream massflow choking was discussed. Then the effects of boundary layer bleeding on the averaged performance parameter of hypersonic inlets, and on the dominant amplitude and frequency of unstart oscillatory flow of hypersonic inlets were presented. The reasons why the boundary-layer bleeding can suppress unstart oscillatory flow of hypersonic inlets were analysed. In conclusion, the averaged performance parameter of hypersonic inlets during a big buzz is improved greatly, and the dominant frequency of unstart oscillatory flow of hypersonic inlets is reduced in contrast with no bleeding, and all these are benefit to the design and operation of hypersonic inlets.

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“…Herrmann (18) and Reinartz (19) studied the effect of varying the isolator length on the hypersonic inlet performance using experimental tests and numerical simulations. Chang (20)(21)(22)(23) used the inlet studied in Refs 18,19 to validate the computational tool used for two-dimensional simulations of the internal compression flows of a hypersonic inlet.…”

Section: Introductionmentioning

confidence: 99%

Numerical validation and back-pressure effect on internal compression flows of typical supersonic inlet

Ding¹,

Shen²,

Huang

et al. 2015

Aeronaut.j.

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A numerical study was conducted to analyse the performance of different turbulence models and different turbulence intensities and turbulence length scales specified for the boundary condition of the inflow to the internal compression flow field of a typical supersonic inlet. The effect of the back-pressure ratio on the properties of the flow field was also investigated. Computational results obtained by the commercial software FLUENT, which is used to solve the full two-dimensional Reynolds-averaged Navier-Stokes equations, were validated through both graphical and quantitative comparisons with previously published experimental data. The two-equation models that were considered in this study are the RNG k-ε, realisable k-ε, standard k-ε, and SST k-ω turbulence models. The RNG k-ε model had the best performance among the four models and predicted good wall pressure distributions. The best agreement between the predicted results and experimental data was obtained when either the default values of the freestream turbulence intensity and length scale in the FLUENT solver were used, or the empirical formula was used to calculate the two parameters of the freestream turbulence properties. The shock wave pattern varied between the oblique mode and the fully developed normal mode with increasing back-pressure ratio, and the unstart phenomenon occurred when the back-pressure ratio was sufficiently high.

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Operation pattern classification of hypersonic inlets

Cited by 33 publications

References 28 publications

Dimethyl 5,5′-methylenebis(2-hydroxybenzoate)

Dimethyl 5,5′-methylenebis(2-hydroxybenzoate)

Effects of boundary-layer bleeding on unstart oscillatory flow of hypersonic inlets

Numerical validation and back-pressure effect on internal compression flows of typical supersonic inlet

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