Article
Engineering, Aerospace
Rasoul Askari, Mohammad Reza Soltani
Summary: A series of wind tunnel tests were conducted to investigate the performance of a Y-shaped diverterless supersonic inlet under different operating conditions. The results showed that the inlet had acceptable performance at its design condition, but experienced significant reduction in performance at high subcritical operating conditions due to asymmetric flow patterns.
Article
Engineering, Aerospace
Javad Sepahi-Younsi, Safa Esmaeili
Summary: An axisymmetric supersonic inlet was studied computationally using the Reynolds-Averaged Navier-Stokes equations and the SST k-omega turbulence model. The study aimed to discover the source of the buzz phenomenon by examining the Ferri and Dailey criteria. The main reasons for the buzz onset were found to be the low-speed flow above the vortex sheet and the flow separation near the cowl lip.
AEROSPACE SCIENCE AND TECHNOLOGY
(2023)
Article
Mechanics
Shijun Sun, Xiaolong Li, Minghao Guo, Jinyu Song, Ce Yang, Jianhua Wang
Summary: This study investigates the influence of inlet Mach number on the aerodynamic performance and flow structure in a supersonic through-flow fan (STFF). It is found that transonic inflow conditions result in greater loss, lower static pressure ratio, and larger flow turning compared to non-transonic inflow conditions. The evolution of shock structure with increasing inlet Mach number is observed. Under different inflow conditions, different factors dominate the blade loss in the STFF cascade. The loss variation under supersonic inflow conditions is mainly caused by the bluntness loss of the leading edge.
Article
Thermodynamics
Yakun Huang, Xiaomin He, Yi Jin, Huanyu Zhu, Zhixin Zhu
Summary: This study reveals that under non-uniform inflow conditions, the velocity peak position and value have a significant impact on combustion performance, leading to asymmetrical flame and temperature distributions.
Article
Engineering, Aerospace
Huacheng Yuan, Fuzhou Liu, Xin Wang, Zhenggui Zhou
Summary: A novel design concept of axisymmetric inlet is proposed based on controllable bleed slots switch to address the problem of starting and inlet-engine matching. By controlling bleeding slots, the inlet achieves minimum starting Mach number and inlet-engine matching, operating well at high total pressure recovery and low exit Mach number.
AEROSPACE SCIENCE AND TECHNOLOGY
(2021)
Article
Engineering, Chemical
Nihan Uygur Babaoglu, Farzad Parvaz, Seyyed Hossein Hosseini, Khairy Elsayed, Goodarz Ahmadi
Summary: The study showed that the inlet cross-sectional shape of a gas cyclone has a significant impact on the flow pattern, pressure drop, and cut-off diameter. Rectangle-shaped inlets generate higher tangential velocities, while different shapes of inlets result in different pressure drops.
Article
Engineering, Aerospace
Yi Jin, Huijun Tan, Hao Zhang, Gaojie Zheng, Shu Sun, Yue Zhang
Summary: Detailed experimental studies are necessary to understand and control the hysteresis during the throat regulation process of a supersonic variable inlet. This study designed a throat variable supersonic inlet and proposed a distributed bleed system to suppress the hysteresis. Experimental results demonstrated that the proposed bleed control effectively decreased the hysteresis loop and achieved successful restart of the inlet.
CHINESE JOURNAL OF AERONAUTICS
(2023)
Article
Engineering, Aerospace
Yu-Jie Wang, Yong -Ping Zhao, Huan Wu, Yi Jin
Summary: This paper experimentally records the pressure signals from a two-dimensional supersonic inlet and analyzes the signals and flow field images to identify the existence of precursor phenomena. A real-time online unstart prediction approach, named CD-WPT-CNN, is proposed by combining change-point detection, wavelet packet, and convolutional neural network. The effectiveness of the approach is verified under test conditions. The experimental results show that the CD-WPT-CNN method outperforms traditional prediction methods and has great application potential.
AEROSPACE SCIENCE AND TECHNOLOGY
(2022)
Article
Engineering, Aerospace
Qian Chen, Huiqiang Zhang
Summary: A new method for inlet condition is proposed to ensure the accuracy of numerical simulation of supersonic reacting mixing layer, avoiding the issues caused by traditional inlet conditions. Numerical simulations and comparisons demonstrate the advantages of the proposed compatible inlet condition.
AEROSPACE SCIENCE AND TECHNOLOGY
(2021)
Article
Engineering, Aerospace
Yu-Jie Wang, Yong -Ping Zhao, Huan Wu, Yi Jin
Summary: In this paper, a combination of change-point detection, wavelet packet transform, and deep learning methods is proposed for real-time online unstart prediction of supersonic inlet. The water cycle algorithm and penalized contrast change-point detection accurately divide the signal into different flow states, providing reliable training data for the subsequent convolutional neural network. A novel network named WPT-CNN is applied for time-frequency domain feature extraction and a multi-channel unstart prediction model is proposed to obtain detailed information inside the supersonic inlet. The results show that the proposed algorithms and models achieve better unstart prediction compared to other methods.
AEROSPACE SCIENCE AND TECHNOLOGY
(2023)
Article
Chemistry, Multidisciplinary
Zhuoran Liu, Caizheng Wang, Ke Zhang, Zhuo Zhao, Zhifeng Xie
Summary: A CFD solver is developed for solving compressible flow problems, utilizing high-order reconstruction schemes and turbulence models to simulate the flow in a two-dimensional supersonic inlet/isolator with high accuracy. Analysis of 2D/3D computation results and refined turbulence simulations using commercial software further investigate flow details near separation areas and boundary layers.
APPLIED SCIENCES-BASEL
(2021)
Article
Engineering, Aerospace
Pedro P. B. Araujo, Marcos V. S. Pereira, George S. Marinho, Joao F. A. Martos, Paulo G. P. Toro
Summary: This work presents a two-dimensional mixed compression scramjet inlet design based on conditions required to burn hydrogen spontaneously at supersonic speeds. The design considers air as a calorically perfect gas and applies the criterion of equal shock strength to determine compression ramps angles and airflow properties. The optimization criteria are extended to analyze the inlet of a scramjet vehicle with 5 compression ramps flying at various speeds and altitudes.
AEROSPACE SCIENCE AND TECHNOLOGY
(2021)
Article
Engineering, Aerospace
Jianbin Li, Jianhan Liang, Mingbo Sun, Zun Cai, Lin Zhang
Summary: This study experimentally investigates the effect of inlet distortion on the combustion process in a direct-connect test environment. The results show that blockage at the entrance of the isolator can accurately mimic the inlet distortion. Combustion enhancement is achieved in cases with blockage, with wider lean blowoff limits in the combustor. The stronger oblique shock wave and additional background shock wave caused by the inlet distortion are the main causes of combustion enhancement in these cases.
AEROSPACE SCIENCE AND TECHNOLOGY
(2023)
Article
Engineering, Chemical
Yuge Yao, Wenshi Huang, Yuxin Wu, Yang Zhang, Man Zhang, Hairui Yang, Junfu Lyu
Summary: The length of the inlet duct may affect the gas flow field and performance of a cyclone separator, with longer ducts leading to higher tangential gas velocity but lower pressure drop and separation efficiency. Expansion loss at the inlet and friction loss inside the cyclone body contribute to the reduction of pressure drop as the inlet duct length increases, with minimal effect once the length is 1.5 times the cylinder diameter.
Article
Engineering, Aerospace
Manami Fujii, Shogo Ogura, Tetsuya Sato, Hideyuki Taguchi, Atsushi Hashimoto, Takashi Takahashi
Summary: The effect of angle of attack on the performance of a supersonic intake is investigated through experimental, numerical, and theoretical investigations. The results show that a positive angle of attack increases the mass capture ratio and total pressure recovery. The total pressure loss caused by a pseudo-shock wave is larger than that of a normal shock wave, and the total pressure loss decreases with a positive angle of attack.
AEROSPACE SCIENCE AND TECHNOLOGY
(2022)
Article
Engineering, Aerospace
Andre F. P. Ribeiro, Carlos Ferreira, Damiano Casalino
Summary: This study compares a filament-based free wake panel method to experimental and validated numerical data in order to simulate propeller slipstreams and their interaction with aircraft components. The results show that the free wake panel method is able to successfully capture the slipstream deformation and shearing, making it a useful tool for propeller-wing interaction in preliminary aircraft design.
AEROSPACE SCIENCE AND TECHNOLOGY
(2024)
