Single expansion ramp nozzle development status

Dusa, D.; Wooten, W. H.

doi:10.2514/6.1984-2455

Cited by 11 publications

(5 citation statements)

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“…Crucial design issues for the thrust nozzle are high performance over the entire flight range and high integration with the airframe. These requirements can best be accomplished by two-dimensional rectangular nozzle configurations (1)(2)(3)(4).…”

Section: Nomenclaturementioning

confidence: 99%

Optimization Aspects of an Ejector Type Hypersonic Thrust Nozzle

Trittler

Eckert

Going

1992

Volume 2: Aircraft Engine; Marine; Microturbines and Small Turbomachinery

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Hypersonic aircraft projects are highly dependant on efficient propulsion systems. High performance and integration within the airframe play a vital role in the overall concept. Particular attention must be paid to the exhaust system that is submitted to a wide range of operational requirements. An optimization of the nozzle geometry for high flight Mach numbers will lead to a low performance at the transonic flight regime. The additional use of secondary ejector air flow at transonic speeds is one option to improve the thrust behaviour of the nozzle. In the presented paper performance data of single expansion ramp ejector type nozzles are predicted using a calculation model based on a method-of-characteristics algorithm. For optimization purposes the effects of various design parameters on axial thrust coefficient and thrust vector angle are discussed. The geometric parameters investigated are the length of the lower nozzle wall and its deflection angle as well as the ejector slot location and its cross-section.

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Section: Nomenclaturementioning

confidence: 99%

Optimization Aspects of an Ejector Type Hypersonic Thrust Nozzle

Trittler

Eckert

Going

1992

Volume 2: Aircraft Engine; Marine; Microturbines and Small Turbomachinery

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“…9 High performance, flexibility, and integration are essential aspects of a nozzle for an aircraft; rectangular nozzles can best meet these requirements. 1,[10][11][12] During the nozzle design, thrust vectoring performance parameters are used to set design parameters. The genetic algorithm (GA) scheme for optimization is based on natural selection and uses the values of the objective function rather than its gradients.…”

Section: Introductionmentioning

confidence: 99%

Multi-objective nozzle design optimization for maximum thrust vectoring performance

Afridi

Khan

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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Thrust vectoring is a promising technology that offers the potential for improved maneuverability, control efficiency, and stealth characteristics of aircraft. Optimized nozzle design over a range of operating conditions is one of the most crucial factors for maximum thrust vectoring operation. Our goal was to investigate the optimal design of bypass dual throat nozzle to maximize thrust vectoring. We performed a multi-objective optimization study by varying the nozzle bypass angle, convergence angle, and bypass width to see what impact these parameters had on the performance of the bypass dual throat nozzle. A steady numerical simulation has been performed on 55 different nozzle configurations to compare their thrust vectoring performance and losses. In all simulations, the k- ϵ turbulence model is used to determine the vectoring states of the nozzle. The computational fluid dynamics analysis was followed by a multi-objective optimization process using the Response Surface Methodology within the ModeFrontier software. The testing of the optimized nozzle shapes using ANSYS FLUENT verified the accuracy and reliability of the multi-objective optimization algorithm. These findings suggest that nozzle convergence does not significantly affect thrust vectoring. In contrast, bypass width and bypass angle significantly affected thrust vectoring.

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“…In literature, the basic nozzle configurations are considered for high Mach number aircraft-the two-dimensional convergent-divergent nozzle and the single expansion ramp nozzle (SERN). [5][6][7][8] The SERN is a configuration originally developed with a hood-type jet deflector stowed in the expansion ramp which would be deployed to provide high vector angles for vertical take off and loading. 5,9 With conventional exhaust system, matching the nozzle exhaust (exit) pressure to the atmospheric condition to optimize thrust force is extremely difficult.…”

Section: Introductionmentioning

confidence: 99%

“…[5][6][7][8] The SERN is a configuration originally developed with a hood-type jet deflector stowed in the expansion ramp which would be deployed to provide high vector angles for vertical take off and loading. 5,9 With conventional exhaust system, matching the nozzle exhaust (exit) pressure to the atmospheric condition to optimize thrust force is extremely difficult. SERN integrated with an airframe is a viable solution to overcome these challenging requirements.…”

Section: Introductionmentioning

confidence: 99%

Experimental investigation of single expansion ramp performance

Kumar

Rathakrishnan

2014

Proceedings of the Institution of Mechanical Engineers, Part G:

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The performance, in terms of thrust augmentation, of a single expansion ramp nozzle (SERN), attached at the exit of a half-covergent-divergent (C-D) nozzle, was investigated experimentally. The nozzle exit Mach number tested was 1.7. The ramp exit was designed for a theoretical Mach number 3.5, based on inviscid theory. Pressure measurements all along the centerline of the ramp plate, with and without side fence, were carried out for half-nozzle operating pressure ratios of 3 to 8. In addition to the pressure measurement, the flow over the ramp plate was visualized with shadowgraph and surface coating. Results show that the thrust augmentation obtained is much lower than the inviscid theoretical prediction. This is because of the flow separation over the ramp and the associated curved shock formed downstream of separation bubble.

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Single expansion ramp nozzle development status

Cited by 11 publications

References 0 publications

Optimization Aspects of an Ejector Type Hypersonic Thrust Nozzle

Optimization Aspects of an Ejector Type Hypersonic Thrust Nozzle

Multi-objective nozzle design optimization for maximum thrust vectoring performance

Experimental investigation of single expansion ramp performance

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