Shock Waves最新文献_第9页

Detonation and shock-induced breakup characteristics of RP-2 liquid droplets RP-2液滴爆轰与激波破碎特性

IF 2.2 4区工程技术

Shock Waves Pub Date : 2023-05-23 DOI: 10.1007/s00193-023-01132-7

S. Salauddin, A. J. Morales, R. Hytovick, R. Burke, V. Malik, J. Patten, S. Schroeder, K. A. Ahmed

{"title":"Detonation and shock-induced breakup characteristics of RP-2 liquid droplets","authors":"S. Salauddin, A. J. Morales, R. Hytovick, R. Burke, V. Malik, J. Patten, S. Schroeder, K. A. Ahmed","doi":"10.1007/s00193-023-01132-7","DOIUrl":"10.1007/s00193-023-01132-7","url":null,"abstract":"<div><p>The deformation and breakup characteristics of liquid rocket propellant 2 (RP-2) droplets are experimentally investigated in a shock tube. The RP-2 droplets are subjected to a weak shock wave, a strong shock, and a detonation wave to deduce the impacts of high-speed and supersonic reacting flows on droplet deformation and breakup. High-speed shadowgraph and schlieren imaging techniques are employed to characterize droplet morphologies, deformation rates, and displacement of the droplet centroid. The results reveal that the transition from a shock wave to a detonation suppresses the deformation of the droplet and augments small-scale breakup. A shift in dominant breakup mechanisms is linked to a significant increase in the Weber number due to an increase in flow velocities and temperatures when transitioning to the detonation case. The experimental data are combined with a droplet stability analysis to predict the “child” (or fragments of the initial “parent” droplet) droplet sizes of each test condition. The child droplet size is shown to decrease as the flow regime transitions toward a detonation. An analytical mass stripping model was also used to determine that the total mass stripped from the parent droplet increased when approaching supersonic reacting conditions. The child droplet sizes and mass stripping rate will ultimately influence evaporation timescales and ignition in supersonic reacting flows, which is important for the development of detonation-based propulsion and power systems.</p></div>","PeriodicalId":775,"journal":{"name":"Shock Waves","volume":"33 3","pages":"191 - 203"},"PeriodicalIF":2.2,"publicationDate":"2023-05-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s00193-023-01132-7.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"4902288","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

New insights into the pre-ignition behavior of methane behind reflected shock waves 反射激波后甲烷预点燃行为的新见解

IF 2.2 4区工程技术

Shock Waves Pub Date : 2023-05-23 DOI: 10.1007/s00193-023-01130-9

J. Caravaca-Vilchez, K. A. Heufer

{"title":"New insights into the pre-ignition behavior of methane behind reflected shock waves","authors":"J. Caravaca-Vilchez, K. A. Heufer","doi":"10.1007/s00193-023-01130-9","DOIUrl":"10.1007/s00193-023-01130-9","url":null,"abstract":"<div><p>Pre-ignition is an undesired combustion event known to restrict kinetic modeling validation. Previous methane oxidation studies reported premature ignition as part of ignition delay time measurements in shock tubes. In this context, the effect on the pre-ignition propensity and auto-ignition behavior of stoichiometric methane mixtures at different dilution levels of <span>(hbox {N}_2)</span>, Ar, He, and <span>(hbox {CO}_2)</span> was studied at 10 bar and 25 bar and temperatures between 1080 K and 1350 K. In addition to conventional sidewall pressure and endwall light emission measurements, a high-speed imaging setup was utilized to visualize the ignition process. Relevant physicochemical parameters to describe and predict the pre-ignition phenomenon were used. The results suggest that dilution levels up to <span>(80%)</span> of bath gas are not successful in mitigating early ignition occurrence and its effects at moderate pressures. Replacing <span>(hbox {N}_2)</span> by He was found to suppress early ignition at 10 bar, attributed to an enhanced dissipation of temperature inhomogeneities in the test gas section. The present findings demonstrate that <span>(hbox {CO}_2)</span> has potential for pre-ignition heat release mitigation, while Ar was confirmed to promote premature ignition. To the best of our knowledge, we present the first detailed study on pre-ignition mitigation for methane mixtures in shock tubes, where further insights into its ignition non-idealities are given.\u0000</p></div>","PeriodicalId":775,"journal":{"name":"Shock Waves","volume":"33 4","pages":"315 - 328"},"PeriodicalIF":2.2,"publicationDate":"2023-05-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s00193-023-01130-9.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"4905285","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

Design and characterization of the Sandia free-piston reflected shock tunnel 桑迪亚自由活塞反射激波隧道的设计与表征

IF 2.2 4区工程技术

Shock Waves Pub Date : 2023-05-23 DOI: 10.1007/s00193-023-01127-4

K. P. Lynch, T. Grasser, R. Spillers, C. Downing, K. A. Daniel, E. R. Jans, S. Kearney, B. J. Morreale, R. Wagnild, J. L. Wagner

{"title":"Design and characterization of the Sandia free-piston reflected shock tunnel","authors":"K. P. Lynch, T. Grasser, R. Spillers, C. Downing, K. A. Daniel, E. R. Jans, S. Kearney, B. J. Morreale, R. Wagnild, J. L. Wagner","doi":"10.1007/s00193-023-01127-4","DOIUrl":"10.1007/s00193-023-01127-4","url":null,"abstract":"<div><p>A new reflected shock tunnel capable of generating hypersonic environments at realistic flight enthalpies has been commissioned at Sandia. The tunnel uses an existing free-piston driver and shock tube coupled to a conical nozzle to accelerate the flow to approximately Mach 9. The facility design process is outlined and compared to other ground test facilities. A representative flight-enthalpy condition is designed using an in-house state-to-state solver and piston dynamics model and evaluated using quasi-1D modeling with the University of Queensland L1d code. This condition is demonstrated using canonical models and a calibration rake. A 25-cm core flow with 4.6-MJ/kg total enthalpy is achieved over an approximately 1-ms test time. The condition was refined using analysis and a heavier piston, leading to an increase in test time. A novel high-speed molecular tagging velocimetry method is applied using in situ nitric oxide to measure the freestream velocity of approximately 3016 m/s. Companion simulation data show good agreement in exit velocity, pitot pressure, and core flow size.</p></div>","PeriodicalId":775,"journal":{"name":"Shock Waves","volume":"33 4","pages":"299 - 314"},"PeriodicalIF":2.2,"publicationDate":"2023-05-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s00193-023-01127-4.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"4905131","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: 6

Linear interaction approximation for shock/disturbance interaction in a Noble–Abel stiffened gas Noble-Abel强化气体中激波/扰动相互作用的线性相互作用近似

IF 2.2 4区工程技术

Shock Waves Pub Date : 2023-05-10 DOI: 10.1007/s00193-023-01131-8

G. Farag, P. Boivin, P. Sagaut

引用次数: 0

Detonation propagation through a diffuse-interface gas layer 通过扩散界面气体层的爆轰传播

IF 2.2 4区工程技术

Shock Waves Pub Date : 2023-04-27 DOI: 10.1007/s00193-023-01128-3

M. McLoughlin, V. Yousefi-Asli, S. Gray, G. Ciccarelli

{"title":"Detonation propagation through a diffuse-interface gas layer","authors":"M. McLoughlin, V. Yousefi-Asli, S. Gray, G. Ciccarelli","doi":"10.1007/s00193-023-01128-3","DOIUrl":"10.1007/s00193-023-01128-3","url":null,"abstract":"<div><p>Detonation propagation in a stratified layer of combustible gas over an inert gas was investigated experimentally. The layer formed in a 12.7-mm-wide channel by opening a sliding door that initially separated a nitrogen-diluted stoichiometric hydrogen–oxygen mixture from argon, or nitrogen. As the lighter combustible gas layer spreads axially down the channel, diffusion across the interface produces a composition gradient across the layer height. A steady detonation wave, generated by deflagration-to-detonation transition in the driver section before the door location, was transmitted into the combustible layer. The axial distance the layer spreads and the amount of mass diffusion across the layer were controlled by the flame ignition delay time after the door opens. Schlieren video and soot foils were used to measure the extent of detonation propagation through the layer. It was shown that detonation propagation through the layer is self-limiting due to over-mixing at the layer leading edge. Three-dimensional numerical simulations, including viscous and multicomponent mass diffusion effects, predicted the composition distribution within the layer. The cell size distribution, calculated based on the theoretical ZND induction zone length, corresponding to the simulation composition distribution showed that a cell size gradient-based failure criterion successfully predicted the extent of propagation in the layer.\u0000</p></div>","PeriodicalId":775,"journal":{"name":"Shock Waves","volume":"33 3","pages":"223 - 236"},"PeriodicalIF":2.2,"publicationDate":"2023-04-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s00193-023-01128-3.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"5027330","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

Control of separation shock unsteadiness in an incident-shock-induced interaction 碰撞-冲击相互作用中分离冲击非定常的控制

IF 2.2 4区工程技术

Shock Waves Pub Date : 2023-04-24 DOI: 10.1007/s00193-023-01129-2

C. Manisankar, S. B. Verma

{"title":"Control of separation shock unsteadiness in an incident-shock-induced interaction","authors":"C. Manisankar, S. B. Verma","doi":"10.1007/s00193-023-01129-2","DOIUrl":"10.1007/s00193-023-01129-2","url":null,"abstract":"<div><p>Separation shock unsteadiness in an incident-shock-induced interaction with and without control is evaluated in a Mach 2.05 flow using a <span>(14^{circ })</span> shock generator. An array of mechanical vortex generators (MVGs) in the form of rectangular vanes (MVG1), ramp vanes (MVG2), and a delta ramp (MVG3) is placed <span>(14delta )</span> upstream of the interaction region (<span>(delta =5.2,{textrm{mm}})</span> being the local boundary layer thickness at the interaction). Among all the devices tested, MVG1 shows a maximum reduction of the separation length (about 28% relative to the no-control case). The spectra at separation also show a shift in the dominant frequency from 220 Hz without control to 539 Hz with MVG1. Interestingly, the peak rms (root mean square) value is seen to occur with control at much larger intermittency values (<span>(upgamma _{upsigma ,{textrm{max}}}=0.92)</span> for MVG1) in contrast to the no-control case in which it occurs at <span>(upgamma _{upsigma ,{textrm{max}}}=0.5)</span> as reported so far. The auto-correlation at the separation and reattachment shock locations indicates the presence of relatively small-scale structures with control as compared to the case without control. Out of all the control cases tested, MVG1 exhibits better separation control with a relatively lower unsteadiness level.\u0000</p></div>","PeriodicalId":775,"journal":{"name":"Shock Waves","volume":"33 2","pages":"81 - 97"},"PeriodicalIF":2.2,"publicationDate":"2023-04-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"4920497","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

Analysis of shock wave acceleration from normal detonation reflection 法向爆轰反射冲击波加速度分析

IF 2.2 4区工程技术

Shock Waves Pub Date : 2023-04-21 DOI: 10.1007/s00193-023-01126-5

D. T. Schoeffler, J. E. Shepherd

引用次数: 0

Shock detachment from curved wedges by local choking: numerical verification 由局部窒息引起的弯曲楔的激波脱离:数值验证

IF 2.2 4区工程技术

Shock Waves Pub Date : 2023-04-18 DOI: 10.1007/s00193-023-01122-9

S. Mölder, A. Gulamhussein

{"title":"Shock detachment from curved wedges by local choking: numerical verification","authors":"S. Mölder, A. Gulamhussein","doi":"10.1007/s00193-023-01122-9","DOIUrl":"10.1007/s00193-023-01122-9","url":null,"abstract":"<div><p>Computational fluid dynamics shows that a shock wave can detach from the sharp leading edge of a curved wedge at a wedge angle smaller than the classical maximum flow deflection as well as the sonic wedge angle. This is attributed to the inability of the sonic flow, at the wedge trailing edge, to pass as much mass flow as is being admitted through the shock wave attached at the leading edge. At this condition, the flow is unsteady, causing both the sonic surface and the shock to make adjustments in their shapes and positions to achieve a steady state with mass-flow balance. As a result, the shock wave becomes detached. Time-accurate CFD calculations show the gasdynamic details of the adjustment where the flow and the detached shock assume a steady state as the mass-flow imbalance gradually decreases to zero. This mechanism of shock detachment, occurring near the leading edge, is called <i>local choking</i> to distinguish it from shock detachment due to global choking that occurs because of flow choking at the exit of a convergent duct and to distinguish it as well from detachment due to an excessive leading-edge deflection. The <i>local choking</i> mechanism has been postulated to be a cause of shock detachment from doubly curved wedges. An analysis, based on curved shock theory and confirmed by CFD, shows that local choking and shock detachment from a doubly curved leading edge are dependent on Mach number, wedge angle, wedge curvature (both streamwise and cross-stream), and wedge length.</p></div>","PeriodicalId":775,"journal":{"name":"Shock Waves","volume":"33 2","pages":"131 - 147"},"PeriodicalIF":2.2,"publicationDate":"2023-04-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"4710642","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

Development of simple evaluation system for Hugoniot of polymethyl methacrylate 聚甲基丙烯酸甲酯Hugoniot简易评价系统的开发

IF 2.2 4区工程技术

Shock Waves Pub Date : 2023-04-12 DOI: 10.1007/s00193-023-01121-w

Y. Takahashi, S. Kubota, T. Saburi

{"title":"Development of simple evaluation system for Hugoniot of polymethyl methacrylate","authors":"Y. Takahashi, S. Kubota, T. Saburi","doi":"10.1007/s00193-023-01121-w","DOIUrl":"10.1007/s00193-023-01121-w","url":null,"abstract":"<div><p>The Hugoniot shock wave velocity <span>((U_{textrm{S}}))</span>–particle velocity <span>((u_{textrm{p}}))</span> curve of polymethyl methacrylate (PMMA) was measured in an experiment using only 2.5 g of a high explosive. The thickness of the plate was varied to accurately determine <span>(U_{textrm{S}})</span> at an arbitrary position in the PMMA. Image analysis was conducted to obtain the <i>x</i>–<i>t</i> diagram of shock wave propagating in PMMA along the axis of the explosive, and its derivative was used to obtain the on-axis <span>(U_{textrm{S}})</span> at an arbitrary location. Using the pressure measurement results and <span>(U_{textrm{S}})</span> values, the Hugoniot <span>(U_{textrm{S}})</span>–<span>(u_{textrm{p}})</span> curve of PMMA was obtained by calculating <span>(u_{textrm{p}})</span> from the momentum conservation law. The results are in very good agreement with the reported values for flat-plate impact experiments conducted using an impact gun. It was found that the Hugoniot <span>(U_{textrm{S}})</span>–<span>(u_{textrm{p}})</span> curve of PMMA on the low-pressure side <span>((u_{textrm{p}} < 0.5, {textrm{km}}/{textrm{s}}))</span> can be evaluated with high accuracy using a simple measurement method that does not use plane waves.\u0000</p></div>","PeriodicalId":775,"journal":{"name":"Shock Waves","volume":"33 2","pages":"169 - 176"},"PeriodicalIF":2.2,"publicationDate":"2023-04-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s00193-023-01121-w.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"4481581","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

Turbulence modeling of 3D high-speed flows with upstream-informed corrections 具有上游信息修正的三维高速流动湍流建模

IF 2.2 4区工程技术

Shock Waves Pub Date : 2023-04-12 DOI: 10.1007/s00193-023-01123-8

C. Prasad, D. V. Gaitonde

{"title":"Turbulence modeling of 3D high-speed flows with upstream-informed corrections","authors":"C. Prasad, D. V. Gaitonde","doi":"10.1007/s00193-023-01123-8","DOIUrl":"10.1007/s00193-023-01123-8","url":null,"abstract":"<div><p>Turbulence modeling has the potential to revolutionize high-speed vehicle design by serving as a co-equal partner to costly and challenging ground and flight testing. However, the fundamental assumptions that make turbulence modeling such an appealing alternative to its scale-resolved counterparts also degrade its accuracy for practical high-speed configurations, especially when fully 3D flows are considered. The current investigation develops a methodology to improve the performance of turbulence modeling for a complex Mach 8.3, 3D shock boundary layer interaction (SBLI) in a double fin geometry.A representative two-equation model, with low-Reynolds-number terms, is used as a test bed. Deficiencies in the baseline model are first elucidated using benchmark test cases involving a Mach 11.1 zero pressure gradient boundary layer and a Mach 6.17 flow over an axisymmetric compression corner. From among different possibilities, two coefficients are introduced to inhibit the non-physical over-amplification of (i) turbulence production and (ii) turbulence length-scale downstream of a shock wave. The coefficients rely on terms already present in the original model, which simplifies implementation and maintains computational costs. The values of the coefficients are predicated on the distribution of turbulence quantities upstream of the shock; this ensures that the modifications do not degrade the model predictions in simpler situations such as attached boundary layers, where they are unnecessary. The effects of the modifications are shown to result in significant improvements in surface pressure and wall heat flux for the 3D SBLI test case, which contains numerous features not observed in 2D situations, such as 3D separation, skewed boundary layers, and centerline vortices. Considerations on the inflow values of turbulence variables and mesh resolution are provided.\u0000</p></div>","PeriodicalId":775,"journal":{"name":"Shock Waves","volume":"33 2","pages":"99 - 115"},"PeriodicalIF":2.2,"publicationDate":"2023-04-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s00193-023-01123-8.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"4484200","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