Internal flowfield characteristics of a scramjet inlet at Mach 10

Wie, D. M. Van; Ault, David A.

doi:10.2514/3.24005

Cited by 39 publications

(9 citation statements)

References 4 publications

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“…Present results agree with the experimental results in the literature. 15 Present results shown that separation region is formed if Mach number at the beginning of isolator is 0.4M 1 due to increase of shock strength. As predicted in the literature, 10 it is shown that when the Mach number the beginning of isolator is decreased below 50%M 1 separation region is developed.…”

Section: Discussionmentioning

confidence: 54%

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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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Section: Discussionmentioning

confidence: 54%

“…15 It is found that cowl position is one of the important parameter for operation of scramjet inlet. Design requirements of isolator being the system which connects inlet and combustion chamber were reported in the literature.…”

Section: Introductionmentioning

confidence: 99%

A new approach for the design of hypersonic scramjet inlets

Raj

Venkatasubbaiah

2012

Physics of Fluids

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“…The 2-D mixed compression inlet [5,32] is used to validate the reliability of the solver code. The mixed external/ internal compression inlet with a flat, horizontal cowl contains a forebody, which turns the flow outward using a combination of a blunted wedge and isentropic turning.…”

Section: Code Validationmentioning

confidence: 99%

Flow characteristics of hypersonic inlets with different cowl-lip blunting methods

Yue

Chang

2014

Sci. China Phys. Mech. Astron.

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Under hypersonic flight conditions, the sharp cowl-lip leading edges have to be blunted because of the severe aerodynamic heating. This paper proposes four cowl-lip blunting methods and studies the corresponding flow characteristics and performances of the generic hypersonic inlets by numerical simulation under the design conditions of a flight Mach number of 6 and an altitude of 26 km. The results show that the local shock interference patterns in the vicinity of the blunted cowl-lips have a substantial influence on the flow characteristics of the hypersonic inlets even though the blunting radius is very small, which contribute to a pronounced degradation of the inlet performance. The Equal Length blunting Manner (ELM) is the most optimal in that a nearly even reflection of the ramp shock produces an approximately straight and weak cowl reflection shock. The minimal total pressure loss, the lowest cowl drag, maximum mass-capture and the minimal aeroheating are achieved for the hypersonic inlet. For the other blunting manners, the ramp shock cannot reflect evenly and produces more curved cowl reflection shock. The Type V shock interference pattern occurs for the Cross Section Cutting blunting Manner (CSCM) and the strongest cowl reflection shock gives rise to the largest flow loss and drag. The cowl-lip blunted by the other two blunting manners is subjected to the shock interference pattern that transits with an increase in the blunting radius. Accordingly, the peak heat flux does not fall monotonously with the blunting radius increasing. Moreover, the cowl-lip surface suffers from severe aerothermal load when the shear layer or the supersonic jet impinges on the wall.

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“…Only in a few studies the pressure and heat transfer coefficient distributions within an air-inlet were investigated [6,8,14,21]. Some additional possibilities for studying the heat transfer and the flow structure within an air-inlet appeared thanks to the application of panoramic investigation methods based on the use of luminescent coatings and transparent air-inlet walls.…”

mentioning

confidence: 99%

Leading edge bluntness effect on the flow in a model air-inlet

et al. 2014

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Flow in an idealized air-inlet with plane walls and a rectangular cross-section is experimentally investigated. The air-inlet is mounted on a plate, at a distance well removed from its leading edge. The experiments were conducted in a Ludwig tube at M ∞ = 5 and Re ∞L = 23 × 10 6 and 13 × 10 6 . A panoramic (optical) technique of measuring the heat transfer coefficient is for the first time applied to study the internal flow in an air-inlet. The data on the effect of the bluntness of the leading edges of the plate and the air-inlet cowl on the heat transfer coefficient distribution and the flow structure within the air-inlet are obtained. It is shown that in an air-inlet with large channel constriction an even small bluntness of the plate or the cowl can lead to global changes in the flow structure.

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Internal flowfield characteristics of a scramjet inlet at Mach 10

Cited by 39 publications

References 4 publications

A new approach for the design of hypersonic scramjet inlets

A new approach for the design of hypersonic scramjet inlets

Flow characteristics of hypersonic inlets with different cowl-lip blunting methods

Leading edge bluntness effect on the flow in a model air-inlet

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