Shock Waves最新文献_第2页

Peculiarities of self-ignition of a hydrogen–air mixture in shock tubes of different roughnesses 不同粗糙度激波管内氢气-空气混合气自燃特性研究

IF 1.7 4区工程技术

Shock Waves Pub Date : 2024-12-14 DOI: 10.1007/s00193-024-01203-3

A. V. Skilandz, O. G. Penyazkov, A. I. Leonchik

{"title":"Peculiarities of self-ignition of a hydrogen–air mixture in shock tubes of different roughnesses","authors":"A. V. Skilandz, O. G. Penyazkov, A. I. Leonchik","doi":"10.1007/s00193-024-01203-3","DOIUrl":"10.1007/s00193-024-01203-3","url":null,"abstract":"<div><p>The induction time in shock tubes with different surface roughnesses and different mixture densities was measured, local features of self-ignition were described, and the results obtained were compared with the results for tubes with other diameters in order to determine the effect of gasdynamic parameters on the formation of ignition kernels and ignition in general. It was discovered that ignition at temperature range of 904–1200 K for <span>(rho _{textrm{5}} = 2.80,{hbox {kg/m}}^{textrm{3}})</span> and 1020–1120 K for <span>(rho _{textrm{5}} = 1.53,{hbox {kg/m}}^{textrm{3}})</span> is determined by the ignition kernel that forms near the tube axis and is a consequence of the gasdynamic effect at the tube axis (axial effect), but is not explained by the adiabatic compression of the mixture due to the expansion of gas from the reflected shock wave bifurcation stagnation region. An increase in the size of the bifurcation structure due to an increase in tube surface roughness does not affect ignition at these temperatures, but expands the ignition range at lower temperatures, in which multi-kernels or volumetric ignition is observed.</p></div>","PeriodicalId":775,"journal":{"name":"Shock Waves","volume":"35 1","pages":"77 - 88"},"PeriodicalIF":1.7,"publicationDate":"2024-12-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143373291","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Predicting terrain effects on blast waves: an artificial neural network approach 预测地形对冲击波的影响：一种人工神经网络方法

IF 1.7 4区工程技术

Shock Waves Pub Date : 2024-12-11 DOI: 10.1007/s00193-024-01206-0

R. Leconte, S. Terrana, L. Giraldi

{"title":"Predicting terrain effects on blast waves: an artificial neural network approach","authors":"R. Leconte, S. Terrana, L. Giraldi","doi":"10.1007/s00193-024-01206-0","DOIUrl":"10.1007/s00193-024-01206-0","url":null,"abstract":"<div><p>Large yield airbursts generate powerful outdoor blast waves. Over long propagation distances, the blast is significantly altered by the topographical relief. Usually, the terrain effects are quantified by running accurate but expensive hydrodynamics or CFD codes. We present an alternative approach based on artificial neural networks, which is applicable wherever the blast–relief interaction can be approximated by an axisymmetric configuration. A database of overpressures associated with a very large sample of the French topography is constructed by running a high-fidelity hydrodynamics code. The proposed neural networks then learn the relationship between the relief geometry and the ground overpressures. The predictive ability of the networks is assessed extensively over a test database for several error metrics. <span>({97}{%})</span> of the peak overpressure predictions can be considered accurate for most practical purposes, and the pressure impulse predictions are even more accurate. Finally, specific artificial neural networks able to estimate the model uncertainties are presented and their performances are discussed.</p></div>","PeriodicalId":775,"journal":{"name":"Shock Waves","volume":"35 1","pages":"37 - 55"},"PeriodicalIF":1.7,"publicationDate":"2024-12-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s00193-024-01206-0.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143373275","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Investigation of flow characteristics of various-aspect-ratio rectangular nozzles with an aft deck 带后甲板的不同展弦比矩形喷管流动特性研究

IF 1.7 4区工程技术

Shock Waves Pub Date : 2024-11-30 DOI: 10.1007/s00193-024-01188-z

W.-L. Chen, W.-H. Huang, W.-H. Lai

{"title":"Investigation of flow characteristics of various-aspect-ratio rectangular nozzles with an aft deck","authors":"W.-L. Chen, W.-H. Huang, W.-H. Lai","doi":"10.1007/s00193-024-01188-z","DOIUrl":"10.1007/s00193-024-01188-z","url":null,"abstract":"<div><p>This study presents an experimental and numerical investigation to characterize the plume pattern of a high-aspect-ratio rectangular convergent/divergent nozzle with an aft deck in under-expanded conditions. The function of an aft deck is to shield the infrared signal of an exhaust plume at its strongest intensity located at the immediate downstream region of the nozzle exit. However, this practice may cause undesirable plume deflection, which needs to be reduced as much as possible. The nozzle pressure ratios ranged from 2 to 4, and the effect of the nozzle exit aspect ratio was examined using wall static pressure measurements and schlieren visualization for cold flows. The experimental setup involved a 3D-printed aft deck nozzle made of acrylonitrile butadiene styrene material, which underwent surface smoothing using acetone vapor. Numerical simulations were conducted using the commercial STARCCM<span>(^{mathrm {+}})</span> software to analyze static pressure ratio variations at the aft deck. The investigation revealed that a nozzle pressure ratio of 3 induced a downward plume deflection at aspect ratio values of 6.77 and 7.54, while an increased aspect ratio of 8.35 resulted in the horizontal ejection of the plume. Moreover, at an aspect ratio of 8.35, the plume was ejected horizontally for nozzle pressure ratios ranging from 2 to 4. At a nozzle pressure ratio of 4, the flow separated from the deck without reattaching, and the plume moved horizontally with minimal deflection. The findings suggest that a combination of a high aspect ratio and sufficiently high nozzle pressure ratio can effectively reduce plume deflection.</p></div>","PeriodicalId":775,"journal":{"name":"Shock Waves","volume":"34 6","pages":"527 - 538"},"PeriodicalIF":1.7,"publicationDate":"2024-11-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s00193-024-01188-z.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142761947","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Normal shock wave coherence relative to other flow events with high and low levels of inlet Mach wave unsteadiness 正常激波相干性相对于其他流动事件与高和低水平的进口马赫波不稳定

IF 1.7 4区工程技术

Shock Waves Pub Date : 2024-11-27 DOI: 10.1007/s00193-024-01202-4

W. Manneschmidt, P. M. Ligrani, M. Sorrell, A. M. Ciccarelli, B. Weigand

{"title":"Normal shock wave coherence relative to other flow events with high and low levels of inlet Mach wave unsteadiness","authors":"W. Manneschmidt, P. M. Ligrani, M. Sorrell, A. M. Ciccarelli, B. Weigand","doi":"10.1007/s00193-024-01202-4","DOIUrl":"10.1007/s00193-024-01202-4","url":null,"abstract":"<div><p>Considered are interactive relationships between a normal shock wave and the downstream shock wave leg of the associated lambda foot, as well as between a normal shock wave and time-varying static pressure as measured along the bottom surface of the test section. Such relationships are investigated as they vary with two different magnitudes of inlet unsteady Mach wave intensity and are characterized using shadowgraph flow visualization data, as well as power spectral density, magnitude-squared coherence, and time lag data. Employed for the investigation is a specialty test section with an inlet Mach number of 1.54, as utilized within a transonic/supersonic wind tunnel. The resulting data provide evidence of distinct interactions over a wide range of frequencies between the normal shock wave and the downstream shock wave leg of the lambda foot for low inlet unsteady Mach wave intensity. Note that these are not present in the same form and over the same ranges of frequency with high inlet unsteady Mach wave intensity. These differences are partially due to the location where flow events originate. The most significant sources of flow unsteadiness within the present investigation are mostly associated with the normal and oblique shock waves (with low inlet unsteady Mach wave intensity), and mostly with inlet flow disturbances from unsteady Mach waves (with high inlet unsteady Mach wave intensity). The present experimental results additionally evidence important connections between the normal shock wave and unsteady flow events within lower portions of the lambda foot, especially near the adjacent boundary layer separation region.</p></div>","PeriodicalId":775,"journal":{"name":"Shock Waves","volume":"34 6","pages":"497 - 513"},"PeriodicalIF":1.7,"publicationDate":"2024-11-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142761866","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Numerical and experimental study of underwash effect and its role in blast-induced traumatic brain injury 下洗效应及其在爆炸致创伤性脑损伤中的作用的数值与实验研究

IF 1.7 4区工程技术

Shock Waves Pub Date : 2024-11-16 DOI: 10.1007/s00193-024-01183-4

S. S. Santhanam, P. Alagappan

{"title":"Numerical and experimental study of underwash effect and its role in blast-induced traumatic brain injury","authors":"S. S. Santhanam, P. Alagappan","doi":"10.1007/s00193-024-01183-4","DOIUrl":"10.1007/s00193-024-01183-4","url":null,"abstract":"<div><p>The blast wave interactions with the helmet–head assembly can result in localized pressure amplification at certain locations around the head. The underwash effect is a typical example of such interaction in the gap between the suspension-type combat helmet and the head. There are hypotheses in the literature that suspect an increase in the severity of blast-induced traumatic brain injury due to combat helmet usage under blast loading. But the literature lacks concrete experimental visual evidence for the underwash effect and the cause–effect relationship between the underwash effect and brain injury. Firstly, in this study, shock wave interactions causing the underwash effect are visualized using the schlieren imaging technique. Secondly, a reasonable correlation between a significantly large, localized pressure amplification due to the underwash effect and the brain’s mechanical stress response was observed with an idealized helmet–head model in a coupled Eulerian–Lagrangian framework. But further studies are needed with more realistic models to prove their significance in the design of blast-resistant combat helmets.</p></div>","PeriodicalId":775,"journal":{"name":"Shock Waves","volume":"34 6","pages":"609 - 624"},"PeriodicalIF":1.7,"publicationDate":"2024-11-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142761662","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

The simultaneous macroscopic and mesoscopic numerical simulation of metal spalling by using the fine-mesh finite element—smoothed particle hydrodynamics adaptive method 采用细网格有限元-光滑颗粒流体力学自适应方法对金属剥落过程进行宏观和细观同步数值模拟

IF 1.7 4区工程技术

Shock Waves Pub Date : 2024-11-06 DOI: 10.1007/s00193-024-01195-0

J. T. Ma, Q. G. He, X. W. Chen

{"title":"The simultaneous macroscopic and mesoscopic numerical simulation of metal spalling by using the fine-mesh finite element—smoothed particle hydrodynamics adaptive method","authors":"J. T. Ma, Q. G. He, X. W. Chen","doi":"10.1007/s00193-024-01195-0","DOIUrl":"10.1007/s00193-024-01195-0","url":null,"abstract":"<div><p>It is extremely important to predict the growth, aggregation, and coalescence failure of voids during the dynamic tensile fracture of ductile metals. In the present work, we used the finite element—smoothed particle hydrodynamics (FE-SPH) adaptive method to simulate the plate impact of tantalum simultaneously from macro- and meso-scales. For macro simulation results, the spallation phenomena and free-surface velocity were in good agreement with the experimental results, verifying the correctness of the simulation method and material model. Moreover, the free surface velocity profiles simulated by the FE-SPH adaptive method is closer to the experiment than those by the finite element method. According to the magnified details of the damage, we envisaged that the deleted elements are converted to SPH particles to represent the formation of voids. By comparing the porosity, we demonstrated the rationality of this envisagement and determined the fine mesh size to simulate growth, aggregation, and coalescence of actual meso-voids. On this basis, we proposed a void-position tracking method to accurately track the temporal and spatial information of voids. Such information would provide a detailed range of damage and describe the features and macro factors affecting void evolution. In general, the fine mesh FE-SPH method can well predict the damage distribution of spallation simultaneously in macro- and meso-scales, and this simple method has important applications.\u0000</p></div>","PeriodicalId":775,"journal":{"name":"Shock Waves","volume":"34 6","pages":"569 - 589"},"PeriodicalIF":1.7,"publicationDate":"2024-11-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142761770","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Higher-order moments of the Mott-Smith shock approximation 莫特-史密斯激波近似的高阶矩

IF 1.7 4区工程技术

Shock Waves Pub Date : 2024-10-25 DOI: 10.1007/s00193-024-01201-5

S. Boccelli

引用次数: 0

Numerical simulation of shock attenuation with real gas effects and a turbulent boundary layer in the expansion tube 考虑真实气体效应和膨胀管内湍流边界层的激波衰减数值模拟

IF 1.7 4区工程技术

Shock Waves Pub Date : 2024-10-14 DOI: 10.1007/s00193-024-01198-x

H. Sakamoto, S. Sato, N. Ohnishi

引用次数: 0

A numerical study of laminar/transitional shock–boundary layer interaction on a hypersonic double wedge using a modified (gamma )-transition model 高超声速双楔上层流/过渡激波-边界层相互作用的改进(gamma ) -过渡模型数值研究

IF 1.7 4区工程技术

Shock Waves Pub Date : 2024-10-04 DOI: 10.1007/s00193-024-01187-0

R. C. DiviaHarshaVardini, G. Rajesh, K. Arul Prakash

{"title":"A numerical study of laminar/transitional shock–boundary layer interaction on a hypersonic double wedge using a modified (gamma )-transition model","authors":"R. C. DiviaHarshaVardini, G. Rajesh, K. Arul Prakash","doi":"10.1007/s00193-024-01187-0","DOIUrl":"10.1007/s00193-024-01187-0","url":null,"abstract":"<div><p>Accurate prediction of the shock–boundary layer interactions (SBLIs) region, encompassing boundary layer separation, reattachment, and transition, is crucial for high-speed flows due to its impact on the aerothermodynamics and performance, particularly at hypersonic speed. Among various types of compression ramp SBLI (laminar, turbulent, or transitional), several experimental and numerical investigations on turbulent SBLI are available in the literature. However, very few RANS-based numerical studies exist on the high-speed laminar/transitional SBLI due to the complexity of modeling the boundary layer transition in hypersonic flows. This study numerically analyzes boundary layer transition and the SBLI interaction region of a double-wedge configuration at hypersonic speeds using a modified <span>(gamma )</span>-transition model. An in-house solver developed with a transition model and SST <i>k</i>–<span>(omega )</span> turbulence model is utilized for this study. A parametric analysis is also carried out to study the effect of wall temperature, wedge length, and wedge angle on the interaction region and transition for various types of compression ramp SBLI. The separation region of the boundary layer and the transition location were estimated using numerical schlieren and Stanton numbers for different parameters. The results show that the modified <span>(gamma )</span>-model predicts the boundary layer separation, reattachment, and transition of laminar/transitional SBLI appropriately compared to a fully turbulent model for all considered parameters.</p></div>","PeriodicalId":775,"journal":{"name":"Shock Waves","volume":"34 6","pages":"515 - 525"},"PeriodicalIF":1.7,"publicationDate":"2024-10-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142761994","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Detonation behaviors in a curved tube with and without an obstacle 有和无障碍物弯曲管内的爆轰行为

IF 1.7 4区工程技术

Shock Waves Pub Date : 2024-10-01 DOI: 10.1007/s00193-024-01200-6

Y. Zeng, H.-H. Ma, F. Yuan, Y. Ge, L.-Q. Wang

{"title":"Detonation behaviors in a curved tube with and without an obstacle","authors":"Y. Zeng, H.-H. Ma, F. Yuan, Y. Ge, L.-Q. Wang","doi":"10.1007/s00193-024-01200-6","DOIUrl":"10.1007/s00193-024-01200-6","url":null,"abstract":"<div><p>Experiments were conducted to investigate detonation propagation in a curved tube filled with stoichiometric 2H<span>(_{2}+)</span>O<span>(_{2}+)</span>7Ar and CH<span>(_{4}+)</span>2O<span>(_{2})</span>. The test section of the experimental setup was a semicircular channel with an internal radius of 500 mm. Detonation velocities were calculated based on the arrival time of the wave front, monitored by pressure transducers. The detonation cellular evolution was recorded using smoked foils. The results revealed that after crossing the obstacle, the detonation wave failed and promptly re-initiated. It then decayed from an overdriven detonation to a steady-state detonation. The detonation development processes were divided into five regimes. The formation of the boundary behind the obstacle and the generation mechanism of the overdriven detonation were thoroughly analyzed. The formation of the boundary behind the obstacle is associated with the curved shock front and the non-uniform cellular structure. The re-initiation distance for an unstable mixture in a curved tube was significantly shorter than that in a straight channel. In the absence of the obstacle, the cell width decreased radially outward, a linear relationship was determined. The speed of the detonation wave initially decreased and then gradually increased.</p></div>","PeriodicalId":775,"journal":{"name":"Shock Waves","volume":"34 6","pages":"555 - 567"},"PeriodicalIF":1.7,"publicationDate":"2024-10-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142761687","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0