Inverse design method on scramjet nozzles based on maximum thrust theory

Yu, Kaikai; Chen, Yile; Huang, Shuai

doi:10.1016/j.actaastro.2019.10.024

Cited by 21 publications

(2 citation statements)

References 18 publications

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“…Their proposed method can increase the axial thrust coefficient, lift, and pitching moment of the nozzle by 5.5%, 1098.2%, and 20.3%, respectively. Yu [8] proposed an inverse design method of the nozzle based on maximum thrust theory and MOC, thereby improving the thrust coefficient, lift, and pitching moment by 31.8%, 201%, and 56.6%, respectively. Subsequently, Yu [9] developed a nozzle design method based on the inverse design method, which can constrain the absolute size and position of the inlet and outlet.…”

Section: Introductionmentioning

confidence: 99%

Maximum thrust nozzle based on height constraint

Huang,

Xu,

2023

Preprint

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Hypersonic aircraft focuses more on the integration of aircraft and engine than ordinary aircraft owing to high performance requirements, and the nozzle design is reflected in the required large area ratio of nozzle inlet and outlet and the compactness of the overall size of the aircraft. In this study, the height constraint is directly introduced into the maximum thrust nozzle design method. A new method for designing nozzles under the height constraints that consults the maximum thrust theory is proposed. Initially, the condition that the nozzle reaches the maximum thrust under the height constraint is deduced mathematically. Then, a nozzle design method satisfying the height constraint is computed using the method of characteristics (MOC). Subsequently, the influence of the design parameters on the design method is studied parametrically. Results show that Mach number scale and asymmetrical factors can affect ramp length and flap length of the nozzle, respectively. These factors great influence the axial thrust performance and lift under a specific height constraint. Compared with the traditional truncation design method, the thrust coefficient and lift increased by 11.93% and 138.45% respectively.

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Section: Introductionmentioning

confidence: 99%

Maximum thrust nozzle based on height constraint

Huang,

Xu,

2023

Preprint

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“…Ju et al (2017) proposed a new concept of increasing the aerodynamic performance of scramjet nozzles by heating the internal flow field, and numerical results show that the thrust coefficient, lift coefficient and pitch moment coefficient increase by 1.55%, 47.27% and 2.53%, respectively. Yu et al (2020a) analyzed the influence of the nozzle length of the scramjet nozzle on the aerodynamic performance of the nozzle. Yu et al (2020b) also studied the influence of flow conditions on the aerodynamic performance of scramjet nozzles, including Mach number, flow deflection angle and ratio of mass flow rate.…”

Section: Introductionmentioning

confidence: 99%

Combined effects of inlet airflow temperature and upper expansion angle on the performance of scramjet nozzle

Sun

Duan

et al. 2022

AEAT

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Purpose The purpose of this paper is to study the combined effects of inlet airflow temperature and the expansion angle of the upper expansion surface (upper expansion angle) on the performance of the scramjet nozzle. Design/methodology/approach The Spalart-Allmaras turbulence two-dimensional model of the nozzle is established for the study. The influence of inlet airflow temperature on the performance of the nozzle is analyzed by detecting the change of the wall pressure of the nozzle. The three angles are chosen for the upper expansion angle (βb) in the model: 8°, 12° and 16°. The temperature of inlet airflow is 600–1,800 K. Findings The study results show that when the βb is 8° and 16°, the wall pressure of the nozzle has a complicated and large fluctuation with the inlet airflow temperature, while the wall pressure has little change as βb is 12°; the thrust coefficient, pitching moment coefficient and lift coefficient of the nozzle fluctuate greatly with the increase of the inlet airflow temperature when βb is 8° and 16°, while the thrust coefficient, pitching moment coefficient and lift coefficient have little fluctuation as βb is 12°. Originality/value The study of the combined effects of the inlet airflow temperature and upper expansion angle on the performance of the scramjet nozzle can provide guidance for the design of scramjet nozzles.

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Over-expanded separation transitions of single expansion ramp nozzle in the accelerating and decelerating processes

2020

Aerospace Science and Technology

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Inverse design method on scramjet nozzles based on maximum thrust theory

Cited by 21 publications

References 18 publications

Maximum thrust nozzle based on height constraint

Maximum thrust nozzle based on height constraint

Combined effects of inlet airflow temperature and upper expansion angle on the performance of scramjet nozzle

Over-expanded separation transitions of single expansion ramp nozzle in the accelerating and decelerating processes

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