Analysis of time accurate pressure measurements in a ramjet /scramjet inlet configuration

Emami, Saied; Rodi, Patrick E.; Trexler, Carl A.; Beaulieu, W.

doi:10.2514/6.1995-37

Cited by 4 publications

(17 citation statements)

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“…In this study, a 2D mixed-compression supersonic intake geometry, experimentally studied by Emami et al, 9 has been considered for the simulation. The intake is designed for a shock-on-lip Mach number of 6.0 and is tested at Mach number of about 4.03 in the ramjet mode of operation.…”

Section: Computational Methodologymentioning

confidence: 99%

“…Unstart might occur because of (i) geometric effects: (a) over contraction or variation in operating conditions to lower Mach number such that the flow becomes subsonic before isolator 7 and (b) unexpected distortion of the incoming inlet flow because of separation of boundary-layer due to SWBLIs (glancing or incident) as a result of variation in angle-of-attack, Reynolds number as well as wall temperature conditions. 8,9 However, it should be noted that practically in presence of the cowl shock, in all the above cases the triggering mechanism is mostly SWBLI. Second, because of (ii) operational effect: that is, excess combustor backpressure condition when the terminal shock is expelled upstream of the cowl.…”

Section: Introductionmentioning

confidence: 91%

“…Second, because of (ii) operational effect: that is, excess combustor backpressure condition when the terminal shock is expelled upstream of the cowl. 9 For the convenience of reference, in this paper, we shall name the first unstart mechanism as “unstart because of SWBLI” and second type as only “unstart.”…”

Section: Introductionmentioning

confidence: 99%

“…Several studies have been carried out in the literature to provide an understanding of the effects of different internal geometric concepts (for supersonic diffuser, isolator, and subsonic diffuser), 9–12,15 upstream flow conditions 13,14 as well as the various active and passive boundary-layer control methods 2,10–14 on intake performance, with an aim to design efficient intakes. Conventionally, to evaluate the effects of these design parameters experimental approach (wind tunnel testing) has been adopted.…”

Section: Introductionmentioning

confidence: 99%

“…Here, a rectangular supersonic intake has been considered and is analyzed at Mach 4.03, corresponding to a unit Reynolds number of approximately 6.9 ×10 7 m −1 . The predicted results have been validated with the available experimental data of Emami et al, 9 and then the flowfield information from CFD is used to evaluate the performance characteristics. Further, the effects of several cowl and isolator configurations on intake performance and “unstart because of SWBLI” are investigated.…”

Section: Introductionmentioning

confidence: 99%

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Computation of viscous flow characteristics of a supersonic intake using eddy-viscosity turbulence models

Pattnaik

Rajan

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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Results of numerical investigation of flow and performance characteristics of a rectangular supersonic intake experimentally tested at Mach number of 4.03 are presented. The viscous flowfield has been obtained by solving Favre averaged Navier–Stokes equations with two eddy viscosity turbulence models, namely, Mentor’s baseline (BSL) k-ω and shear stress transport (SST) k-ω models. In addition, the effect of wall temperature conditions as well as several configurations of cowl and isolator are simulated to validate the computational methodology. The analysis has been carried out at a freestream Mach number of 4.03 and 0° angle-of-attack, corresponding to a unit Reynolds number of about 6.9×107 m−1. The predicted boundary-layer and the wall static pressure distribution using SST k-ω model shows better agreement with the experimental data compared to the BSL model and hence indicates superior capability to capture the onset and the amount of flow separation due to SWBLIs. Moreover, the terminal shock structure at different operating modes as well as the “unstart because of SWBLIs” is predicted quite accurately using the model. The wall temperature condition is found to have a strong effect on the amount of flow separation at the cowl and the subsequent interactions. Further, the results show that the sidewalls have a marginal effect on the centerline wall static pressure, though a three-dimensional flowfield with two stream-wise vortices are observed close to it as a result of the swept SWBLIs of the cowl shock with the sidewall boundary-layer leading to a higher loss in performance.

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Section: Computational Methodologymentioning

confidence: 99%