Article
Mechanics
Mohammad Javad Pour Razzaghi, Yasin Masoumi, Seyed Mojtaba Rezaei Rezaei Sani, Guoping Huang
Summary: This study numerically analyzed the control of a separation bubble behind a ramp by introducing a fluid microjet. The results showed that the microjet could effectively reduce the size of the separation bubble, and using a three-jet array had a better performance compared to a single jet.
Article
Computer Science, Interdisciplinary Applications
Raja Mangalagiri, Satya P. Jammy
Summary: This study numerically explores the influence of sidewalls in a three-dimensional context for ramp-induced shock-wave boundary layer interactions (RSWBLI) and compares it with impinging-type shock-wave boundary layer interactions (ISWBLI). The results show that the introduction of sidewalls leads to different separation characteristics in RSWBLI compared to ISWBLI, and the extent of sidewall separation is limited. This study is important for understanding the characteristics of SWBLI.
COMPUTERS & FLUIDS
(2023)
Article
Mechanics
Shengtai He, Kai Zhang, Yukuan Song, Yu Zhou
Summary: This study experimentally investigates the control of flow separation over a two-dimensional curved ramp using a spanwise steady-blowing slit jet. The relationship between separation bubble sizes or pressure coefficient at the end of the ramp and jet velocity ratio is found. It is also discovered that flow separation from the ramp can be completely suppressed with a small jet angle, but not with a large jet angle.
Article
Physics, Applied
Chuan-Biao Zhang, He-Sen Yang, Hua Liang, Shan-Guang Guo
Summary: An experimental investigation was conducted to study the control effects of the high-frequency streamwise pulsed arc discharge array (HS-PADA) on the double compression ramp shock wave/boundary layer interaction (DCR-SWBLI) at Mach 2.0. The results showed that the 20 kHz actuation was more effective in weakening the shock wave intensity compared to the 10 kHz actuation. The HS-PADA exhibited two different control effects: modifying the shock structure related to the separation zone and modifying the low-frequency unsteadiness of the shock wave, which may not be related to the separation zone. The first separation shock wave was more sensitive to the HS-PADA compared to the second. The control mechanism of the HS-PADA on DCR-SWBLI was extracted.
JOURNAL OF PHYSICS D-APPLIED PHYSICS
(2022)
Article
Engineering, Aerospace
Aniruddha Ajay Kane, Ravi K. Peetala, Vinayak Kulkarni
Summary: This study numerically investigates the control of shock-induced boundary layer separation using a pressure feedback technique (PFT). The results show that the injection location has minimal effect on the separation reduction capability of PFT, while the suction location greatly influences its performance. The optimum suction location shifts with changes in freestream conditions.
Article
Engineering, Aerospace
Liang Chen, Yue Zhang, Hong-chao Xue, Hui-jun Tan, Zi-yun Wang, Hang Yu
Summary: This study investigates the flow phenomenon of ramp shock/boundary layer interaction on supersonic/hypersonic flight vehicles using single-sided and double-sided flow models. The single-sided model focuses on the curved ramp shock/boundary layer interaction near the corner of the inlet, while the double-sided model exposes the coupling mechanism and evolution process near the symmetry plane of the inlet.
AEROSPACE SCIENCE AND TECHNOLOGY
(2023)
Article
Engineering, Aerospace
Hao Xu, Wei Huang, Zhao-bo Du, Yu-shan Meng, Chao-yang Liu, Li Yan
Summary: Boundary layer separation is a common issue in supersonic/hypersonic vehicles, which can negatively impact the lift coefficient. Current active flow control techniques using microjets have shown to effectively prevent such separation by generating counter-rotating vortex pairs that mix low-energy and high-energy flows. The size of the vortex core plays a crucial role in the control of supersonic wall boundary layer interaction (SWBLI). The pressure ratio and geometry of the microjet holes also affect the control effectiveness and total pressure recovery coefficient.
AEROSPACE SCIENCE AND TECHNOLOGY
(2023)
Article
Mechanics
Zongnan Chen, Jiaao Hao, Chih-Yung Wen
Summary: The control performance of a pulsed nanosecond dielectric barrier discharge (NSDBD) plasma actuator on a supersonic compression corner was studied using experiments and numerical simulations. The results showed that the plasma actuator can effectively reduce the separation bubble length and suppress the separation region by modifying the flow structures, when appropriately applied in terms of voltage and location.
Article
Mechanics
H. M. Broadley, R. E. Hewitt, J. S. B. Gajjar
Summary: In this study, we investigate high Reynolds number supersonic flow over a compression ramp in the triple-deck formulation. Previous studies have shown rapid growth of high-frequency disturbances in initial-value computations, but the physical or numerical origin of these instabilities remains unidentified. By analyzing linear perturbations and considering the integral eigenrelation proposed by Tutty and Cowley, we demonstrate that the observed instabilities do not follow the expected growth rate. We solve both temporal and spatial instability problems at large wavenumbers and find that the growth rate of the instability is dominated by higher-order terms in the expansion.
JOURNAL OF FLUID MECHANICS
(2023)
Article
Engineering, Aerospace
Ziao Wang, Juntao Chang, Chen Kong, Yunfei Li
Summary: Experimental investigation was conducted on micro-ramps for shock train control in a Mach 1.85 supersonic isolator flow, revealing that taller devices generate stronger wake and wave structures for better control. The wake and wave structures eliminate the Mach stem in the shock train leading edge, inhibit boundary layer thickening, slow down supersonic core flow contraction, and promote high total pressure fluid downstream development. The wake structure promotes shock train oscillation and upstream motion, whereas the wave structure restrains oscillation and enhances resistance backpressure downstream.
Article
Physics, Fluids & Plasmas
Stephan Priebe, M. Pino Martin
Summary: The study conducted DNS of a hypersonic shock wave/turbulent boundary layer interaction. The results showed consistent behavior with experimental observations. The shock wave interaction with the boundary layer was analyzed and compared with experimental data.
PHYSICAL REVIEW FLUIDS
(2021)
Article
Engineering, Aerospace
Kao-Chun Su, Kung-Ming Chung, Sergey Isaev
Summary: This study investigates the impact of installing VGs upstream of the convex corner on shock-induced boundary layer separation. The findings indicate that increasing the VG height reduces the occurrence of boundary layer separation induced by shock waves but also leads to a decrease in lift.
INTERNATIONAL JOURNAL OF AEROSPACE ENGINEERING
(2022)
Article
Computer Science, Interdisciplinary Applications
Fulin Tong, Junyi Duan, Xinliang Li
Summary: This study investigates the shock wave and supersonic turbulent boundary layer interaction in a double compression ramp with fixed ramp angles at Mach 2.9 through direct numerical simulations. The research reveals that increasing the distance between the two ramp kinks can significantly reduce the size of the separation region and affect flow structures, turbulence properties, etc.
COMPUTERS & FLUIDS
(2021)
Article
Mechanics
Shibin Cao, Jiaao Hao, Igor Klioutchnikov, Herbert Olivier, Chih-Yung Wen
Summary: Direct numerical simulations are used to study hypersonic flow over a compression ramp, revealing the formation of streamwise heat flux streaks downstream of reattachment that exhibit low-frequency unsteadiness and are non-uniformly distributed in the spanwise direction. The unsteadiness of the heat flux streaks is coupled with a pulsation of the reattachment position, and global instabilities are found to be responsible for the flow unsteadiness.
JOURNAL OF FLUID MECHANICS
(2021)
Article
Mechanics
Yizhou Wang, Haideng Zhang, Yun Wu, Yinghong Li, Yujie Zhu
Summary: This paper investigates the flow control effects of nanosecond dielectric barrier discharge (NS-DBD) plasma actuation on the supersonic compressor cascade flow at low Reynolds numbers through large-eddy simulations. The study shows that NS-DBD plasma actuation induces a distorted flow structure (DFS) on both the blade pressure surface and suction surface. Despite being suppressed by shock waves on the blade pressure surface, the DFS still triggers instability in the shear layer. The study also finds that the DFS on the blade pressure surface suppresses shock-wave-induced large-scale flow separation and reduces the overall total pressure loss of the blade passage by 7.4%.
Article
Engineering, Aerospace
Akriti Tripathi, C. Manisankar, S. B. Verma
AEROSPACE SCIENCE AND TECHNOLOGY
(2015)
Article
Mechanics
Shashi B. Verma, Manisankar Chidambaranathan
Article
Mechanics
S. B. Verma, C. Manisankar
Article
Engineering, Aerospace
S. B. Verma, C. Manisankar
Article
Thermodynamics
Aqib Khan, Rakesh Kumar, Shashi Bhushan Verma, C. Manisankar
EXPERIMENTAL THERMAL AND FLUID SCIENCE
(2018)
Article
Mechanics
S. B. Verma, C. Manisankar
Article
Mechanics
S. B. Verma, C. Manisankar, P. Akshara
Article
Engineering, Aerospace
S. B. Verma, C. Manisankar
Article
Computer Science, Interdisciplinary Applications
T. Nilavarasan, G. N. Joshi, A. Misra, C. Manisankar, S. B. Verma
Summary: The study evaluated the effect of 'ramped vane'-type vortex generators on shock-induced flow separation near an axisymmetric compression corner. By placing these devices at different positions upstream of the compression corner, significant changes were observed in the shock-boundary layer interaction flowfield, leading to transformation of separation bubble structures and widening of attached flow zones.
JOURNAL OF VISUALIZATION
(2021)
Article
Mechanics
Shashi Bhushan Verma, C. Manisankar
Summary: An experimental investigation was conducted to study the control of separation characteristics induced by a 24 degrees compression corner in Mach 2.0 flow. The study focused on the effect of different parameters, such as inter-VG spacing, vane chord length, and vane angle, on the interaction and surface flow topology. The results showed that reducing inter-VG spacing and modifying the VG configuration can significantly reduce separation and improve pressure recovery. The use of mechanical vortex generators helped stabilize the interaction by splitting a large separation bubble into smaller individual separation cells.
Article
Mechanics
T. Nilavarasan, G. N. Joshi, A. Misra, C. Manisankar, S. B. Verma
Summary: Experiments conducted at Mach 2 demonstrated the effectiveness of Ramped Vanes (RVs) in delaying shock-induced flow separation. By manipulating the incoming boundary layer, RVs generated counter-rotating vortices that altered the flowfield, resulting in a delayed onset of separation. The height of the RVs played a significant role, with taller devices yielding a more pronounced reduction in separation length.
EUROPEAN JOURNAL OF MECHANICS B-FLUIDS
(2022)
Article
Mechanics
Shashi Bhushan Verma, Manisankar Chidambaranathan
Summary: This experimental investigation examines the effect of an array of inclined co-rotating vanes on a three-dimensional interaction generated by a semi-infinite sharp fin. The study finds that using vanes with a smaller chord length and larger height can effectively control the interaction, reducing pressure and separation shock strength.
Article
Engineering, Aerospace
Tamizhazhi Korkkai Vendan Nilavarasan, Ganapati Narasimha Joshi, Ajay Misra, Chidambaranathan Manisankar, Shashi Bhushan Verma
Summary: This study evaluates the effectiveness of five different micro vortex generator geometries in reducing flow separation. The results showed that the design with ramped vanes was the most effective in enhancing momentum and reducing separation.
PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING
(2023)
Article
Mechanics
Manisankar Chidambaranathan, Ishan Singh, Sathia Narayanan, Shashi Bhushan Verma
Summary: An experimental investigation was conducted to study off- and on-surface flow developments behind various mechanical vortex generator configurations at Mach 2.0. The study found that the velocity profile is much fuller for rectangular vane relative to other control configurations, and the iso-velocity contours captured the wake growth and vortex liftoff features for all the control configurations. The quantitative data from these tests further helped to understand the flow development features in detail.
Article
Engineering, Aerospace
S. B. Verma, C. Manisankar