A quasi one-dimensional bleed flow rate model for terminal normal shock stability in mixed compression supersonic inlet

Li, Qiushi; Yongzhao, Lv; Li, Shaobin

doi:10.1177/0954406213519975

Cited by 4 publications

(2 citation statements)

References 17 publications

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“…Empirical fits for this modified turning angle were then derived based on experimental data, improving the accuracy of Bunnag's model. Li et al [11] studied the use of a pair of bleed slots to stabilize the terminal shock waves located at the throat of a hybrid hypersonic inlet. A quasi-one-dimensional bleed flow model with two bleed cavities in an equal sectional flow passage was established, such that the bleed mass-flow rate was a function of the position of the normal shock waves.…”

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confidence: 99%

Supersonic Bleed Rate Model for a Circular Orifice Based on Geometric Similarity

et al. 2020

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On the basis of the geometric similarity between polygons and circles, a bleed rate model of a supersonic inviscid circular hole is first established through a gradual approximation by regular polygons. The bleed mass-flow rate depends on the parameters at the entrance. A supersonic inviscid bleed choking model is further established by using the inflow Mach number and the pressure ratio when the expansion wave is parallel to the entrance. For a depthless hole at Mach 2.0 and with a pressure ratio of 0.5, the difference of flow coefficient predicted by the present model to that of computational fluid dynamics is 1.4% under nonchoking conditions. Under choking conditions with a pressure ratio of 0.1, the difference is 3.1%. Furthermore, the influence of the boundary layer on the bleed mass-flow rate is transformed into the influence of the displacement thickness on the effective size of the bleed hole. Based on that, the viscous bleed rate model is established, which shows a maximum error of 7.7% for a depthless bleed hole over laminar flow at Mach 4.0 and Reynolds number 2.590 × 10 5 . Compared with the reported results of the full bleed hole, the difference of the bleed mass-flow rate predicted by the present model is 3.8%.

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Supersonic Bleed Rate Model for a Circular Orifice Based on Geometric Similarity

et al. 2020

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“…On the other hand, the mixed compression type demonstrates higher e ciency at this range and o ers many bene ts over the other types. 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.…”

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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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Development of a coupled supersonic inlet-fan Navier–Stokes simulation method

Lyu

Pan

et al. 2018

Chinese Journal of Aeronautics

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A quasi one-dimensional bleed flow rate model for terminal normal shock stability in mixed compression supersonic inlet

Cited by 4 publications

References 17 publications

Supersonic Bleed Rate Model for a Circular Orifice Based on Geometric Similarity

Supersonic Bleed Rate Model for a Circular Orifice Based on Geometric Similarity

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

Development of a coupled supersonic inlet-fan Navier–Stokes simulation method

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