Calculation of external-internal flow fields for mixed-compression inlets

Chyu, J. J.; Kawamura, Tetuya; Bencze, D. P.

doi:10.1016/0045-7825(87)90031-4

Cited by 4 publications

(2 citation statements)

References 23 publications

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“…To the present time, no PAW workshop featured a similar case, and to the authors' best knowledge, no other study validated the performance of an air breathing engine accounting for all those subsystems. Standalone mixed-compression inlet configurations [1] [2] or inlets with vortex generators [3] have been previously shown in the literature, yet the complexity or nature of those cases is different to the one found in a mixed-compression inlet operating at high speeds.…”

Section: Test Case Descriptionmentioning

confidence: 99%

Summary of the 6^th Propulsion Aerodynamics Workshop: NASA 1507 Inlet

Moreno,

Zachos,

Gantt

et al. 2024

AIAA SCITECH 2024 Forum

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The 6 th AIAA Propulsion Aerodynamics Workshop (PAW6) was held as part of AIAA's Science and Technology Forum between January 21 st -22 nd 2023 in National Harbor, US. The goal of the workshop was to evaluate the current capability of computational fluid dynamics (CFD) on complex flows, pertinent to the high-speed propulsion community. PAW6 inlet test case was a mixed-compression supersonic inlet referred to here as the NASA 1507 inlet which featured a complex shock system attached at the entry along with a range of different flow control methods such as porous bleeds and vortex generators. Among several experimental test cases, four were selected for the workshop across a range of back-pressures, or inlet flow ratios, that yield different levels of pressure recovery, engine face distortion and bleed flows. Flow prediction data from 8 different participants was submitted using a total of 5 different computational domains for which 9 computational grids were developed and provided by Cadence. In general, flow predictions were better able to match the test data near the critical point of intake operation regardless of the flow solver, grid refinement level or turbulence model. Models with fully resolved rather than modelled bleed and/or vortex generators showed better results. Across the sub-critical range of operation, a notable under prediction of the flow ratio was seen across all flow solvers and models, indicating significant variations in the porous bleed modelling between the CFD datasets. The work indicates that more effort is needed by the relevant community toward the development of robust predictive capabilities, especially when complex flow control systems are in place for stability across the operating range.

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Section: Test Case Descriptionmentioning

confidence: 99%

Summary of the 6^th Propulsion Aerodynamics Workshop: NASA 1507 Inlet

Moreno,

Zachos,

Gantt

et al. 2024

AIAA SCITECH 2024 Forum

View full text Add to dashboard Cite

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“…Many investigations were dedicated to mixed compression supersonic inlets in recent years, indicating their popularity amongst designers [2][3][4][5][6]. Chyu et al [7] considered a three-dimensional unsteady, compressible ow in a mixed compression inlet. They solved Navier-Stokes equations using a combined implicit-explicit (BeamWarming-Steger/MacCormack) method, and BaldwinLomax algebraic method was used for turbulence modeling.…”

Section: Introductionmentioning

confidence: 99%

Numerical Investigation of Back Pressure and Free-stream Effects on a Mixed Compression Inlet Performance

Ebrahimi

Chavoshi

2017

Scientia Iranica

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Abstract. Inlet performance has an important role in the operation of air-breathing propulsion systems. In this study, performance of a supersonic axisymmetric mixedcompression inlet in the supercritical operating condition is numerically studied. The e ects of free-stream Mach number and engine-face pressure on performance parameters, including mass ow ratio, drag coe cient, total pressure recovery, and ow distortion, are investigated. For this sake, a multi-block density-based nite volume CFD code is developed, and Reynolds-averaged Navier-Stokes equations with Spalart-Allmaras oneequation turbulence model are employed. The code is validated by comparing numerical results against other computational results and experimental data for two test cases of inviscid ow in a two-dimensional mixed-compression inlet and ow in an external compression inlet. Finally, the code is utilized for the investigation of a speci c supersonic mixed-compression inlet with the design Mach number of 2.0 and length-to-diameter ratio of 3.4. Results revealed that the increment of free-stream Mach number leads to the decrease in total pressure recovery and drag coe cient, while mass ow ratio and ow distortion increase. The e ects of engine-face pressure on performance parameters showed that by increasing the engine-face pressure, mass ow ratio and drag coe cient remain constant, while total pressure recovery increases and ow distortion decreases.

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