Preliminary assessment of exhaust systems for high Mach (4 to 6) fighter aircraft

Kuchar, A. P.; Wolf, J.

doi:10.2514/6.1989-2356

Cited by 5 publications

(2 citation statements)

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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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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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“…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%

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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Nozzle design optimization by method-of-characteristics

Goeing

1990

26th Joint Propulsion Conference

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Preliminary assessment of exhaust systems for high Mach (4 to 6) fighter aircraft

Cited by 5 publications

References 0 publications

Multi-objective nozzle design optimization for maximum thrust vectoring performance

Multi-objective nozzle design optimization for maximum thrust vectoring performance

Experimental investigation of single expansion ramp performance

Nozzle design optimization by method-of-characteristics

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