Penetration heights of liquid jets in high-speed crossflows

Lin, Kuo-Cheng; Kennedy, Paul; Jackson, Thomas

doi:10.2514/6.2002-873

Cited by 56 publications

(42 citation statements)

References 11 publications

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“…It is observed that the application of this technique to either mean or standard deviation images yields similar results. In the literature, the most popular technique is the edge detection on the average of images [83]. Nevertheless, working on the standard deviation images is preferred as these images provide better contrast.…”

Section: Penetration Heightmentioning

confidence: 99%

“…All of the existing experimental studies in supersonic cross flow [61,83,107,73,27] focus on penetration height of liquid injected into a cross flow with a Mach number varying between 2 and 4. Among these studies, [27] proposes a more complex correlation for penetration height that is supposed to include a cross flow Mach number range up to 8.6.…”

Section: Research Since 1980'smentioning

confidence: 99%

See 1 more Smart Citation

Experimental Investigation of Liquid Fragmentation In Hypersonic Crossflow

Asma

Masutti

Chazot

2009

27th AIAA Applied Aerodynamics Conference

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Section: Penetration Heightmentioning

confidence: 99%

Section: Research Since 1980'smentioning

confidence: 99%

Experimental Investigation of Liquid Fragmentation In Hypersonic Crossflow

Asma

Masutti

Chazot

2009

27th AIAA Applied Aerodynamics Conference

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“…13. Experimental profiles for circular jet injections into supersonic Mach = 1.94 crossflow based on shadowgraph (Lin et al 2002a) and PDPA measurements (Lin et al 2004) are plotted simultaneously, for comparison. These correlations, which are among the most recent ones in this kind of flow topology with compressible crossflow are chosen because the experimental conditions are identical to this study except for the crossflow Mach number and because of the lack of experimental data for hypersonic crossflows.…”

Section: Penetration Heightmentioning

confidence: 99%

“…They also show that lateral dimension of the jet depends more on the lateral extension of the injector than the momentum-flux ratio. Lin et al (2002a) have proposed one of the newest correlations based on shadowgraph measurements, in which, alike the previous studies, the penetration height relates to the momentum-flux ratio and downstream distance. Lin et al (2004) obtained a similar correlation based on PDPA measurements, differing the constants and powers of the correlation.…”

Section: Introductionmentioning

confidence: 99%

Experimental investigation of liquid jet injection into Mach 6 hypersonic crossflow

et al. 2008

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The injection of a liquid jet into a crossing Mach 6 air flow is investigated. Experiments were conducted on a sharp leading edge flat plate with flush mounted injectors. Water jets were introduced through different nozzle shapes at relevant jet-to-air momentumflux ratios. Sufficient temporal resolution to capture small scale effects was obtained by high-speed recording, while directional illumination allowed variation in field of view. Shock pattern and flow topology were visualized by Schlieren-technique. Correlations are proposed on relating water jet penetration height and lateral extension with the injection ratio and orifice diameter for circular injector jets. Penetration height and lateral extension are compared for different injector shapes at relevant jet-to-air momentumflux ratios showing that penetration height and lateral extension decrease and increase, respectively, with injector's aspect ratio. Probability density function analysis has shown that the mixing of the jet with the crossflow is completed at a distance of x/d j * 40, independent of the momentum-flux ratio. Mean velocity profiles related with the liquid jet have been extracted by means of an ensemble correlation PIV algorithm. Finally, frequency analyses of the jet breakup and fluctuating shock pattern are performed using a Fast Fourier algorithm and characteristic Strouhal numbers of St = 0.18 for the liquid jet breakup and of St = 0.011 for the separation shock fluctuation are obtained.

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“…Mixing enhancement devices are employed in scramjet combustor such as physic ramp and aerodynamic ramp (Wang, Song, Li, & Cai, 2008) injectors, strut injectors and atomization technology for liquid fuel. The aerated-liquid jet (Lin, Kirkendall, Kendedy, & Jackson, 1999;Lin, Kendedy, & Jackson, 2000;2002) being developed for years has proved its effect on reducing the liquid droplet diameter and improving for the local equivalence ratio if the gas is air or oxygen (Segal, 2009). (4) Air throttle technical.…”

Section: Introductionmentioning

confidence: 99%

Experimental Research on Hydrogen and Hydrocarbon Fuel Ignition for Scramjet at Ma=4

Zhang¹,

Le²,

Yang³

et al. 2013

MAS

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Ignition experiments of Hydrogen and Ethylene were performed on direct-connected pulse combustion facility. Air stagnation temperatures were 900 K and stagnation pressures were 0.8 MPa, the entrance Mach number was approximate 2.0 provided by a two-dimension nozzle. The experimental results indicate that: (1) Hydrogen self-ignition won't occur at stagnation 935 K when it is injected upstream the cavity in this combustor model. But with low input power igniter, hydrogen can be ignited reliably. (2) Ethylene cannot be ignited with igniter only even at high igniter power. Under the assistant of both igniter and pilot Hydrogen, Ethylene can be ignited reliably and maintain stable combustion after the igniter and pilot hydrogen completely turned off. (3) The lowest equivalence ratio of pilot hydrogen for successful ethylene ignition is 0.05 below that ignition will fail. (4) When pilot hydrogen and igniters were both employed for ignition, the function of igniter is to ignite the hydrogen and the input power of igniter has no influence on ignition performance.

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Penetration heights of liquid jets in high-speed crossflows

Cited by 56 publications

References 11 publications

Experimental Investigation of Liquid Fragmentation In Hypersonic Crossflow

Experimental Investigation of Liquid Fragmentation In Hypersonic Crossflow

Experimental investigation of liquid jet injection into Mach 6 hypersonic crossflow

Experimental Research on Hydrogen and Hydrocarbon Fuel Ignition for Scramjet at Ma=4

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