Research on Supersonic Inlet Bleed

Davis, David O.; Vyas, Manan A.; Slater, John W.

doi:10.2514/6.2012-272

Cited by 22 publications

(19 citation statements)

References 6 publications

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“…In previous work, such as Davis (Ref. 6) and Willis (Ref. 2), it has been shown that flow coefficient curves are largely self-similar for a bleed plate configuration and as such multiple Mach numbers are easily plotted on the same graph.…”

Section: Results and Data Analysis Overviewmentioning

confidence: 99%

Effect of Boundary-Layer Bleed Hole Inclination Angle and Scaling on Flow Coefficient Behavior

Eichorn

Barnhart

Davis

et al. 2013

51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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Section: Results and Data Analysis Overviewmentioning

confidence: 99%

Effect of Boundary-Layer Bleed Hole Inclination Angle and Scaling on Flow Coefficient Behavior

Eichorn

Barnhart

Davis

et al. 2013

51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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“…Information has primarily been restricted to flow coefficients and boundary layer velocity profiles both with and without an impinging oblique shock wave, [14][15][16][17] with only a few glimpses of the more complex 3D flow structure surrounding individual bleed holes, 18,19 which can be seen in figure 2, and their interaction within an array.…”

Section: B Previous Workmentioning

confidence: 99%

Comparison of Experimental and Computational Flow Structure Investigations of a Normal-Hole Bled Supersonic Boundary Layer

Oorebeek

Babinsky

Ugolotti

et al. 2014

32nd AIAA Applied Aerodynamics Conference

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A series of experiments have been conducted on an array of bleed holes spanning the width of the CUED supersonic wind tunnel at Mach numbers of 1.8 and 2.5. The wind tunnel was run with varying levels of suction, and the resulting flow structure over the bleed array was subsequently mapped with a Laser Doppler Velocimetry (LDV) system at a resolution of 0.25 hole diameters or better. The same wind tunnel setup was also simulated using the OVERFLOW Navier-Stokes equation solver. Overall good agreement was found in the definition of the expansion fan and barrier shock pattern produced by flow entering the normal holes, with the production of streamwise vorticity noted in both CFD and experimental studies. The proposed mechanism of vorticity generation is an effect of the barrier shock standing off from the rear edge of each bleed hole, and is predicted by CFD to increase in strength as Mach number increases, as well as when the vorticity is produced by a single hole, rather than an array. Both studies found that vorticity decreases as suction strength is reduced, however the experimental study showed the vortices persist farther downstream than predicted by CFD.

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“…На начальном этапе исследований усилия были сосредоточены на изучении общих характеристик систем слива и их влияния на структуру течения и запуск воздухозаборника [7]. Анализ известных исследований свидетельствует, что разработка систем слива воздуха для входных устройств базируется на экспериментальных данных и эмпирических зависимостях, которые играют решающую роль в процессе моделирования таких течений [8][9][10]. В результате этих исследований было показано, что при организации слива ПС на поверхностях сжатия воздухозаборника приходится сталкиваться со сложными проблемами, от решения которых зависит расход сливаемого воздуха и его влияние на эффективность работы входного устройства.…”

Section: Introductionunclassified

Influence of Flow Speed on the Compression Surfaces of Inlet on Efficiency of the Boundary Layer Bleed

Goldfeld

2019

SJPhys

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The paper presents the results of analytical and experimental study of the bleed coefficient at high flight Mach numbers from 3 to 7. For the calculation, an analytical model was used model with a fixed exit in the supercritical bleed mode, which allows varying the bleed air mass depending on flow conditions and parameter bleed system. The measurement of the bleed flow coefficients were performed for three bleed configurations in a wind tunnel at local Mach numbers in front of the bleed area from 2.5 to 5.96. The model had a long forebody, so that before the bleed area there was a thick boundary layer. As a result, new experimental data on bleed coefficient and its general dependence on the Mach numbers up to 6 and the bleed angles of 90 and 45° were obtained. It is revealed that at increase in the local Mach number, the tendency is observed towards a decrease in the bleed coefficient, and this tendency intensifies with decrease in the bleed channel inclination. These data were used to evaluate known analytical models to determine the characteristics of bleed systems at hypersonic flow velocity analytical models to determine the characteristics of bleed systems at hypersonic flow velocity.

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Research on Supersonic Inlet Bleed

Cited by 22 publications

References 6 publications

Effect of Boundary-Layer Bleed Hole Inclination Angle and Scaling on Flow Coefficient Behavior

Effect of Boundary-Layer Bleed Hole Inclination Angle and Scaling on Flow Coefficient Behavior

Comparison of Experimental and Computational Flow Structure Investigations of a Normal-Hole Bled Supersonic Boundary Layer

Influence of Flow Speed on the Compression Surfaces of Inlet on Efficiency of the Boundary Layer Bleed

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