Numerical investigation of axisymmetric intake flowfield and performance for scramjet-powered ascent flight

Fujio, Chihiro; Brahmachary, Shuvayan; Ogawa, H.

doi:10.1016/j.ast.2021.106531

Cited by 16 publications

(3 citation statements)

References 27 publications

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“…Fujio and Ogawa [16] presented a multi-objective design optimization based on deep learning to predict flowfields inside scramjet intakes that could replace CFD simulations. Posteriorly, results of recent researches demonstrated that higher compression efficiency can be achieved at lower Mach number while total pressure losses can be minimized at higher Mach numbers and altitude [17,18]. Despite these dispositions achieve the thermodynamic condition sufficiently adequate to fuel self-ignition condition [14,17,18] a disadvantage of these configurations is the need of more longer scramjet lengths to accommodate conical shock wave structures, which are positioned closest to wall surfaces at high Mach numbers.…”

Section: Introductionmentioning

confidence: 99%

“…Posteriorly, results of recent researches demonstrated that higher compression efficiency can be achieved at lower Mach number while total pressure losses can be minimized at higher Mach numbers and altitude [17,18]. Despite these dispositions achieve the thermodynamic condition sufficiently adequate to fuel self-ignition condition [14,17,18] a disadvantage of these configurations is the need of more longer scramjet lengths to accommodate conical shock wave structures, which are positioned closest to wall surfaces at high Mach numbers. Based on this, more studies are needed to elucidate the main flow phenomena in other alternatives of internal compression systems, and consequently, define the best geometry for scramjet engines.…”

Section: Introductionmentioning

confidence: 99%

“…This multi-ramp methodology was not tested in internal symmetrical systems, except for axisymmetric geometries [14,[16][17][18], so more detailed studies on planar are needed.…”

Section: Introductionmentioning

confidence: 99%

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Conceptual study of a scramjet with symmetrical internal compression system

Araújo,

Bezerra,

Souza

et al. 2024

Preprint

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This paper focuses on the design analysis of a planar hydrogen-powered scramjet constructed with a symmetrical internal compression system of rectangular cross-sectional area, developed to demonstrate supersonic combustion in atmospheric flight at 30 km of altitude and velocity of 2050 m/s, equivalent to Mach number 6.8. In this analysis, is proposed an analytical approach based on theories of oblique shock wave optimized by the criterion of maximum total pressure recovery, Rayleigh flow’s and the area ratio coupled to Prandtl–Meyer to dimension the compression, combustion, and expansion sections. The design of the compression system was developed to provide velocity, and temperature sufficiently adequate for spontaneous supersonic combustion of the hydrogen-air mixture. The atmospheric airflow was modeled by the hypothesis of calorically perfect gas without viscous effects. A visualization of the effects of various flow phenomena, such as shock waves, combustion, and expansion waves, on the evolution of thermodynamic properties throughout the scramjet demonstrator is discussed. The results showed by conducted compression performance analysis, a major increase in entropy in the reflected shock wave where the criterion of shock waves of equal strength was not applied. Also, the airflow thermodynamic properties and velocity from the leading edge to the trailing edge were analyzed. With heat addition, the scramjet was able to produce uninstalled thrust.

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