Design considerations for supersonic micronozzles

Louisos, William; Alexeenko, Alina; Hitt, Darren L.; Zilic, Adis

doi:10.1504/ijmr.2008.016453

Cited by 48 publications

(20 citation statements)

References 36 publications

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“…The explanation for the weak, local maximum in efficiency for the full spike at Re ∼ 150 is not immediately clear; however, such behavior has been observed for linear nozzles on the micro-scale. 12 To reiterate a previous point, unlike macro-scale aerospike designs where thrust-to-weight ratio is a key factor, micro-scale aerospike design can be based effectively on performance. Therefore the use of full-length spikes should be the target design, in as much as microfabrication techniques permit.…”

Section: Numerical Resultsmentioning

confidence: 93%

Numerical Simulations of Supersonic Flow in a Linear Aerospike Micro Nozzle

Zilic

Hitt

Alexeenko

2007

37th AIAA Fluid Dynamics Conference and Exhibit

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In this study, we numerically examine thrust performance of the linear aerospike nozzle micro-thruster for various nozzle spike lengths and flow parameters in order to identify optimal geometry(s) and operating conditions. Decomposed hydrogen-peroxide is used as the monopropellant in the studies. Performance is characterized for different flow rates (Reynolds numbers) and aerospike lengths, and the impact of micro-scale viscous forces is assessed. It is found that 2-D full micro-aerospike efficiencies can exceed axisymmetric micro-nozzle efficiencies by as much as 10%; however, severe penalties are found to occur for truncated spikes at low Reynolds numbers.

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Section: Numerical Resultsmentioning

confidence: 93%

Numerical Simulations of Supersonic Flow in a Linear Aerospike Micro Nozzle

Zilic

Hitt

Alexeenko

2007

37th AIAA Fluid Dynamics Conference and Exhibit

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“…Nozzles in each array were on a 1 mm center‐to‐center spacing. While C‐D nozzles are often used to accelerate jets to supersonic velocity,16 the proximity of the substrate prevents such acceleration in this case.…”

Section: Widths Of Printed Oled Pixels At Their Full‐width Half‐maximmentioning

confidence: 99%

Vapor‐Phase Microprinting of Multicolor Phosphorescent Organic Light Emitting Device Arrays

McGraw

Forrest

2013

Advanced Materials

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“…2 The challenge is that the flow field is significantly affected by the boundary effects along the nozzle walls. [10][11][12] In this work, linear aerospikes are considered for the study of the kinetic boundary layer (KBL), because they provide the ideal scenario for a diverging two-dimensional surface designed to accelerate the flow by bounding it on only one side.…”

Section: Introductionmentioning

confidence: 99%

Rarefied flow expansion in linear aerospikes

Giovannini

Abhari

2015

Physics of Fluids

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The formation of the kinetic boundary layer (KBL) on diverging surfaces is studied experimentally and computationally. The diverging surfaces are chosen to follow profiles commonly used for linear aerospikes, in order to study the KBL formation in an ideal and two-dimensional flow expansion bounded only on one side. Experiments with different operating conditions at low Re number (from 132 to 2826) and in the transition regime (Kn number from 6.4 to 0.42) are used to evaluate the thickness of the KBL. The ambient pressure, the ratio between the stagnation and surface temperature, the roughness and the shape of the surface are parametrically varied maintaining the same pressure ratio between the total and the ambient pressures. Simulations are validated and used to study the influence of gas-surface interaction on formation of the KBL and to quantify the non-equilibrium state of the flow field. It is shown that the topography of the surface does not influence the growth of the KBL, but the flow can be tailored by modifying the shape of the surface. Using the experimental and computational data, a phenomenological model is developed to predict growth of the KBL. The thickness of the KBL is proportional to the length along the surface and to the mean free path. Furthermore, the ratio between the mean free path on the surface and the thickness of the KBL is found to be an invariant for the diverging surfaces modified through linear corrections. In the aerospike system, the KBL reduces the thrust by 35% and the proposed corrected geometry increases the real thrust by 20%.

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Design considerations for supersonic micronozzles

Cited by 48 publications

References 36 publications

Numerical Simulations of Supersonic Flow in a Linear Aerospike Micro Nozzle

Numerical Simulations of Supersonic Flow in a Linear Aerospike Micro Nozzle

Vapor‐Phase Microprinting of Multicolor Phosphorescent Organic Light Emitting Device Arrays

Rarefied flow expansion in linear aerospikes

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