Optimal supersonic intake design for air collection engines (ACE)

Valorani, Mauro; Nasuti, Francesco; Onofri, Marcello; Buongiorno, C.

doi:10.1016/s0094-5765(99)00185-x

Cited by 14 publications

(7 citation statements)

References 9 publications

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“…For example, it has been shown by Valorani et al (1999) that -if viscous effects are neglected -in the case of a similar intake, critical at M ∞ = 3.5, the total pressure recovery may pass from 0.45 in the subcritical regime to 0.85 in the supercritical one. A correct prediction of the shock shape and of its reflection is therefore required to provide reliable evaluations.…”

Section: Introductionmentioning

confidence: 99%

Theoretical considerations on shock reflections and their implications on the evaluation of air intake performance

Onofri

Nasuti

2001

Shock Waves

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Many theoretical studies have shown the existence of a hysteresis effect in the solution of oblique shock reflections. In fact, a wide domain of free-stream Mach number and shock angle values exists where regular reflection and Mach reflection are both possible solutions for the same flow conditions. Part of this domain overlaps the typical operating conditions of supersonic air intakes, and therefore it is of practical interest to obtain a deeper understanding of the theoretical problem. Indeed, although both solutions are theoretically possible, they yield very different flowfields and consequently large discrepancies in the evaluation of the air intake performance. Numerical solutions for steady configurations have been carried out and compared with the flow evolution obtained for time-dependent cases. The results have confirmed numerically the existence of the multiple solution domain where hysteresis takes place in time-dependent simulations. The analysis of the physical and numerical problems encountered has provided indications for a correct simulation in practical applications.

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Section: Introductionmentioning

confidence: 99%

Theoretical considerations on shock reflections and their implications on the evaluation of air intake performance

Onofri

Nasuti

2001

Shock Waves

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“…However, isentropic condition puts a limit on number of shocks. 3 Moreover, increase in number of shocks implies to decrease in ramp angles and thereby increasing the length of the inlet which adds to overall weight of the scramjet.…”

Section: Design Methodologymentioning

confidence: 99%

“…By employing these two approaches independently, supersonic inlet was designed and the effects of on-design and off-design conditions on performance of inlet at different flight Mach numbers were reported. 3 One of the first attempts in developing an optimal design for supersonic inlet which reduces to subsonic flow was done by Oswatitsch. 4 By using gas dynamic relations and Lagrange multipliers a) E-mail: kvenkat@iith.ac.in. and with an objective of maximum total pressure recovery, a set of oblique shock angles and one terminating normal shock angle were obtained.…”

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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“…Valorani et al [15] has reported the necessity of adoption of bent cowl for mixed compression intake. Studies with bent cowl or suitably curved cowls leads to improvement in performance as reported by Yanagi et al [16], Kubota et al [17], Hermann et al [18], Trapier et al [19], etc.…”

Section: Introductionmentioning

confidence: 99%

Flow Field Investigation of a Rectangular Supersonic Air-Intake With Cowl Bending

Das,

Prasad

2023

joast

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Experimental and computational studies are made on a rectangular mixed compression air-intake designed for Mach 2.2 to study the effect of cowl bending. Flow field details inside the intake have been captured using schlieren flow visualisation and measurement of static and total pressures. Three dimensional simulations have been made with RANS solver adopting k-ω turbulence model using FLUENT. Studies show that the configuration indicate unstart without any cowl bending whereas startup is observed with adoption of small cowl bend. In addition, improvement in quality of flow inside the intake has been observed. In general, agreements between experimental and computational results are good. Studies have been also made at different back pressures. Provision of a small cowl bending could lead to better performance of intake.

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Optimal supersonic intake design for air collection engines (ACE)

Cited by 14 publications

References 9 publications

Theoretical considerations on shock reflections and their implications on the evaluation of air intake performance

Theoretical considerations on shock reflections and their implications on the evaluation of air intake performance

A new approach for the design of hypersonic scramjet inlets

Flow Field Investigation of a Rectangular Supersonic Air-Intake With Cowl Bending

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