Aerodynamic Performance Analysis of a Hypersonic Inlet Isolator Using Computation and Experiment

Reinartz, Birgit; Herrmann, Carsten; Ballmann, J.; Koschel, W.

doi:10.2514/2.6177

Cited by 164 publications

(84 citation statements)

References 12 publications

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“…Экспериментальным, теоретическим и численным исследованиям сверхзвуковых течений в каналах с псевдоскачком посвящено большое количество теоретических и практических ра-бот [3][4][5][6][7][8][9][10][11][12][13]. При этом большинство исследований связано с течениями в цилиндрических или в слегка расширяющихся (1-4°) каналах, которые рассматриваются в качестве диффузоров (изоляторов) для сверхзвуковых воздухозаборников.…”

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Influence of Back Pressure on the Flow in the Diffuser of a Supersonic Air Inlet

2017

PNRPU Aerospace Engineering Bulletin

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Институт теоретической и прикладной механики им. С.А. Христиановича Сибирского отделения РАН, Новосибирск, Россия ВЛИЯНИЕ ПРОТИВОДАВЛЕНИЯ НА ТЕЧЕНИЕ В ДИФФУЗОРЕ СВЕРХЗВУКОВОГО ВОЗДУХОЗАБОРНИКАПредставлены результаты численного исследования перехода от сверхзвукового течения к дозвуковому в диф-фузоре сверхзвукового воздухозаборника прямоточного воздушно-реактивного двигателя при изменении противодав-ления в камере сгорания (при дросселировании канала). Рассматривались два варианта осесимметричного диффузора с большими углами (угол раскрытия θ = 10° и θ = 90°). Получены картины течения в зависимости от геометрических па-раметров диффузора и от степени дросселирования канала. Течение в диффузоре с углом раскрытия θ = 10° соответ-ствует псевдоскачковому режиму течения с отрывными зонами в пограничном слое. Течение в диффузоре с углом рас-крытия θ = 90° соответствует струйному течению в канале. Несмотря на принципиально различные режимы течения, характеристики потока на длине более 8-10 калибров одинаковы. Проведен анализ влияния противодавления на ха-рактеристики перехода (потери полного давления, прирост статического давления, длину переходной зоны и др.). Пока-зано, что при использовании диффузора с большими углами раскрытия противодавление в камере сгорания может из-меняться в три раза, не оказывая влияния на течение в горле и, соответственно, на течение в воздухозаборнике.Ключевые слова: численное моделирование, сверхзвуковой воздухозаборник, диффузор, псевдоскачок, каме-ра сгорания, дросселирование. INFLUENCE OF BACK PRESSURE ON THE FLOW IN THE DIFFUSER OF A SUPERSONIC AIR INLETThe results of a numerical study of the transition from supersonic to subsonic flow in the diffuser of a supersonic air inlet for ramjet engine with a change in the back pressure from the combustion chamber (with channel throttling) are presented. Two variants of an axisymmetric diffuser with large opening angles were considered (angle θ = 10º and θ = 90º). Flow patterns are obtained depending on the geometric parameters of the diffuser and on the degree of channel throttling. The flow in the diffuser with the opening angle θ = 10º corresponds to the pseudo-shock flow regime with separation zones in the boundary layer. The flow in the diffuser with an opening angle θ = 90º corresponds to the jet stream in the channel. Despite the fundamentally difference in flow regimes, the flow characteristics at a length of more than 8-10 calibers are the same. The effect of back pressure on the transition characteristics (total pressure loss, static pressure increase, transition zone length, etc.) is analyzed. It is shown that when a diffusers with large opening angles are used, the back pressure in the combustion chamber can be changed by a factor of three without affecting on the flow in the throat and, accordingly, on the flow in the air inlet.Keywords: numerical simulation, supersonic air inlet, diffuser, pseudo-shock, combustion chamber, throttling. ВведениеПроблема взаимодействия воздухозаборника и камеры сгорания является одной из клю-чевых ...

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Section: ( )unclassified

Influence of Back Pressure on the Flow in the Diffuser of a Supersonic Air Inlet

2017

PNRPU Aerospace Engineering Bulletin

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“…16 Various experimental and computational investigations were performed to know the effect of isolator lengths on performance of scramjet inlet by Reinartz and Hermann. 17 CFD has evolved up to an extent where complex phenomenon of hypersonic propulsions can be modeled and these CFD simulations have become important means to study the physics of scramjet engines. [18][19][20][21][22][23] Various numerical techniques have been used to analyze the scramjet propulsion such as large eddy simulation to model the jet injection in scramjet combustion chamber.…”

Section: Introductionmentioning

confidence: 99%

A new approach for the design of hypersonic scramjet inlets

Raj

Venkatasubbaiah

2012

Physics of Fluids

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A new methodology has been developed for the design of hypersonic scramjet inlets using gas dynamic relations. The approach aims to find the optimal inlet geometry which has maximum total pressure recovery at a prescribed design free stream Mach number. The design criteria for inlet is chosen as shock-on-lip condition which ensures maximum capture area and minimum intake length. Designed inlet geometries are simulated using computational fluid dynamics analysis. The effects of 1D, 2D inviscid and viscous effects on performance of scramjet inlet are reported here. A correction factor in inviscid design is reported for viscous effects to obtain shock-on-lip condition. A parametric study is carried out for the effect of Mach number at the beginning of isolator for the design of scramjet inlets. Present results show that 2D and viscous effects are significant on performance of scramjet inlet. Present simulation results are matching very well with the experimental results available from the literature.

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“…So the classification of different hypersonic inlet operation modes, especial the classification of the inlet backpressure unstart/low Mach number unstart, is necessary to the unstart control of the hypersonic inlet. Unstart phenomena of the hypersonic inlet have been very active fields of research in last decades, there have been many investigations devoted to this subject [5][6][7][8][9][10][11][12][13][14][15][16][17][18][19]. Mayer and Paynter [5,6] used an Euler solver and simulated an axisymmetric inlet unstart due to the variation of freestream variables such as temperature, velocity and pressure.…”

Section: Introductionmentioning

confidence: 99%