Nozzle design optimization by method-of-characteristics

Goeing, M.

doi:10.2514/6.1990-2024

Cited by 14 publications

(5 citation statements)

References 3 publications

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“…The model is truncated 50% considering the nozzle gained is too long. The study [5] shows the truncation can limit the length and weight of the nozzle without affecting the nozzle performance seriously. The geometric parameters of the nozzle are shown in Fig.…”

Section: Physical Modelmentioning

confidence: 99%

Numerical Study of Chemical Non-equilibrium Flow in Hydrocarbon Scramjet Nozzle

Zhang¹,

Li-zi²,

Yu³

2012

Proceedings of the 1st International Conference on Mechanical Engineering and Material Science

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The non-equilibrium flow and frozen flow of hydrocarbon scramjet nozzle were numerically simulated to research the non-equilibrium effects on the nozzle performance. The numerical results show the recombination occurs during the expansion in the scramjet nozzle, which is helpful to the nozzle performance. The calculation results suggest the influence of the inlet mach and the fuel equivalence ratio to the non-equilibrium effects on nozzle performance is visible.

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Section: Physical Modelmentioning

confidence: 99%

Numerical Study of Chemical Non-equilibrium Flow in Hydrocarbon Scramjet Nozzle

Zhang¹,

Li-zi²,

Yu³

2012

Proceedings of the 1st International Conference on Mechanical Engineering and Material Science

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“…An asymmetric single expansion ramp nozzle is applied for thrust generation. The nozzle expansion ramp is defined by a nonparametric spline derived from a method of characteristics for a horizontal exit flow angle [30]. The coordinates of the flaps trailing edge are defined by the combustor outflow cross section and the overall length of the engine and therefore are not independent variables.…”

Section: Engine Configurations and Computational Setupmentioning

confidence: 99%

Probabilistic Aspects of Scramjet Design

Schütte¹,

Staudacher²

2009

Journal of Propulsion and Power

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Scramjet design is characterized by a multitude of design variables influencing a highly nonlinear and complex system. Methods such as mean line calculations, high fidelity computational fluid dynamics, and empirical studies are generally used to derive aircraft engine performance. Because of the high complexity and the incomplete knowledge of hypersonic flow regimes, the question of robust design arises in the given context and leads to the need of probabilistic methodology. In this paper a probabilistic approach to scramjet engine design assessing both inflow and model uncertainty is presented. The two different types of uncertainty are quantified with respect to their different nature by use of a two-step bootstrap methodology. A descriptive sampling Monte Carlo method is employed to propagate the quantified uncertainties through the engine model to exemplify the high sensitivity of net thrust vector to present uncertainties and to analyze the correlation between the parameters variations. Nomenclature A = area, m 2 E i = error vector of the ith component, i 2 0; 31; 4; 7 ;9 (see Fig. 1) F net;x , F net;y = net thrust in x and y directions, N G i = vector of geometrical parameters of the ith component, i 2 0; 31; 4; 7 ;9 (see Fig. 1) h = duct height, m L = segment length, m Ma = Mach number _ m = mass flow, kg s 1 n = surface normal vector p = static pressure, Pa px, px j y = probability of x; probability of x assuming y Re x = Reynolds number S fuel = vector of fuel parameters (see Fig. 1) T = static temperature, K v = velocity, m s 1 X i = vector of deterministic flow parameters of the ith component, i 2 0; 31; 4; 7 ;9 (see Fig. 1) X i = vector of probabilistic flow parameters of the ith component, i 2 0; 31; 4; 7 ;9 (see Fig. 1) = ramp angle, deg = boundary-layer displacement thickness, m = mean value x = spline describing the geometry of the nozzle expansion ramp = flow density, kg m 3

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“…1 The focus often was on optimization of nozzle geometry with direct design methods like the method of characteristics. 2–7 Attempts of nozzle contour optimization were carried out multiple times by means of design methods by analysis including multi-physics CFD simulations together with numerical optimization tools, so called multidisciplinary optimization, but only with respect to the flow inside the nozzle. 8–12 with respect to simple fabrication, a conical C-D nozzle is chosen.…”

Section: Introductionmentioning

confidence: 99%

Investigation of nozzle flow in high altitude test facility

ANL

Sundararaj

Khan

2022

Advances in Mechanical Engineering

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A high altitude test facility was developed for the experimental studies on nozzles for various levels of vacuum. The current study is focused on the performance of the nozzle under various altitude condition and to characterized the high altitude test facility. A supersonic nozzle designed for Mach 2.5 is used for the study. Compressed air is taped from the high pressure plenum having a pressure of 20 bar and is regulated and expanded through the nozzle. The inlet pressures for the study is varied from 4.5 to 10 bar. The nozzle is within the enclosure which is evacuated to 0.7–0.02 bar. Schlieren is used to view the flow condition at the end of the nozzle. A nozzle for 2.5 Mach is designed and tested in HAT facility. The nozzle design is validated with the CFD for various NPR. The high altitude test facility is characterized for various NPR and is found to be optimum flow at 14 NPR for 33 s at an inlet pressure of 4.5.

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Nozzle design optimization by method-of-characteristics

Cited by 14 publications

References 3 publications

Numerical Study of Chemical Non-equilibrium Flow in Hydrocarbon Scramjet Nozzle

Numerical Study of Chemical Non-equilibrium Flow in Hydrocarbon Scramjet Nozzle

Probabilistic Aspects of Scramjet Design

Investigation of nozzle flow in high altitude test facility

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