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International Journal of Hypersonics最新文献

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Numerical Study on Heat Reduction of Various Counterflowing Jets over Highly Blunt Cone in Hypersonic Flow 高超声速高钝锥上不同回流射流减热数值研究
International Journal of Hypersonics Pub Date : 2011-03-01 DOI: 10.1260/1759-3107.2.1.1
M. Gerdroodbary, M. Fayazbakhsh
{"title":"Numerical Study on Heat Reduction of Various Counterflowing Jets over Highly Blunt Cone in Hypersonic Flow","authors":"M. Gerdroodbary, M. Fayazbakhsh","doi":"10.1260/1759-3107.2.1.1","DOIUrl":"https://doi.org/10.1260/1759-3107.2.1.1","url":null,"abstract":"In this paper, the effectiveness of counterflowing jets as heat-reduction devices for large-angle blunt cones flying at hypersonic Mach numbers is numerically simulated with various coolant jets. Different jet conditions have been chosen to investigate the effect of the counterflow jet on the surrounding flow field of nose cone. The compressible, unsteady, axisymmetric Navier-Stokes equations are solved with SST turbulence model for free stream Mach number of 5.75 at 0° angle of attack with and without gas injection. The coolant gas (air, Carbon Dioxide, and helium) is chosen to inject into the hypersonic flow at the nose of the model. The numerical results presented the surface heat reduction for different coolant jets. According to the investigation of various conditions of opposing jets, important phenomena of flow field and some effective jet conditions are found.","PeriodicalId":350070,"journal":{"name":"International Journal of Hypersonics","volume":"3 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2011-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121239972","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
引用次数: 25
Performance Tests of JF-10 High-Enthalpy Shock Tunnel with a FDC Driver 采用FDC驱动的JF-10高焓激波隧道性能试验
International Journal of Hypersonics Pub Date : 2011-03-01 DOI: 10.1260/1759-3107.2.1.29
Zonglin Jiang, J. Lin, W. Zhao
{"title":"Performance Tests of JF-10 High-Enthalpy Shock Tunnel with a FDC Driver","authors":"Zonglin Jiang, J. Lin, W. Zhao","doi":"10.1260/1759-3107.2.1.29","DOIUrl":"https://doi.org/10.1260/1759-3107.2.1.29","url":null,"abstract":"JF-10 detonation-driven high-enthalpy shock tunnel was re-built with a forward detonation cavity (FDC) driver and the experimental data from its performance tests are summarized and reported in this paper. Test-duration of high-enthalpy flows produced with the improved JF10 is found to be extended by two times under the condition that the FDC driver is about 40% shorter than the original one. The uniform pressure area of the thus-obtained hypersonic flows in a 500 mm diameter conical nozzle is about 700 mm in length and 400 mm in diameter. Incident shock wave decay in the driven section appears to be much less by comparing with the original JF-10 shock tunnel. The performance improvement of JF-10 high-enthalpy shock tunnel was demonstrated to be very successful and high quality hypervelocity flows can be generated for aero-thermochemistry experiments.","PeriodicalId":350070,"journal":{"name":"International Journal of Hypersonics","volume":"8 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2011-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121888017","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
引用次数: 5
Effect of Injection Angle in Mixing and Combustion Characteristics of Scramjet Combustor 喷射角对超燃冲压发动机燃烧室混合及燃烧特性的影响
International Journal of Hypersonics Pub Date : 2011-03-01 DOI: 10.1260/1759-3107.2.1.15
M. C. Murty, D. Chakraborty
{"title":"Effect of Injection Angle in Mixing and Combustion Characteristics of Scramjet Combustor","authors":"M. C. Murty, D. Chakraborty","doi":"10.1260/1759-3107.2.1.15","DOIUrl":"https://doi.org/10.1260/1759-3107.2.1.15","url":null,"abstract":"Effect of injection angle in mixing and combustion in a scramjet combustor is numerically simulated. Three dimensional Navier Stokes equations alongwith k-e turbulence model are solved using commercial CFD software. Both infinitely fast rate kinetics and single step finite rate kinetics are used to model chemical kinetics. Turbulence chemistry interaction is modeled by Eddy Dissipation Concept (EDC). Good agreement between the computed and experimental results for angular injection (30°) and perpendicular injection forms the basis of further analysis. More flow blockage has caused significant upstream interaction for perpendicular injection and terminal shock is seen to anchor upstream of combustor step; while for angular injection, the flow field is predominantly supersonic. Single step finite rate chemistry show comparatively low pressure and lesser upstream interaction because of the presence of backward reaction. Thermochemical variables are analysed to study the effect of angle of injection on nature...","PeriodicalId":350070,"journal":{"name":"International Journal of Hypersonics","volume":"9 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2011-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128997745","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
引用次数: 6
Type-VI and Type-V Shock-Shock Interactions on Double-Wedge Geometries Using AUSM+ on Unstructured Grid 非结构网格上双楔几何的vi型和v型冲击-冲击相互作用
International Journal of Hypersonics Pub Date : 2010-12-01 DOI: 10.1260/1759-3107.1.4.225
P. Halder, K. Sinhamahapatra, Navtej Singh
{"title":"Type-VI and Type-V Shock-Shock Interactions on Double-Wedge Geometries Using AUSM+ on Unstructured Grid","authors":"P. Halder, K. Sinhamahapatra, Navtej Singh","doi":"10.1260/1759-3107.1.4.225","DOIUrl":"https://doi.org/10.1260/1759-3107.1.4.225","url":null,"abstract":"The Euler equations are solved on unstructured triangular meshes for hypersonic flow over double-wedge geometries. The driving algorithm is an upwind biased cell centered finite volume method. AUSM+ method is used to split the fluxes. Edney (1968) studied the shock interactions by impinging an externally generated planar oblique shock on the bow shock generated by a cylinder. Depending upon the parametric conditions Edney classified the shock interactions in different types. Two interaction topologies, namely Type-VI and Type-V and the transition from Type-VI to Type-V are studied in details. Both six-shock and seven-shock configurations of Type-V interaction are presented.","PeriodicalId":350070,"journal":{"name":"International Journal of Hypersonics","volume":"8 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131200536","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
引用次数: 5
Self Ignition of Hydrogen-Air Mixtures with Inclined Porthole Injection in Supersonic Flows 超音速流动中倾斜舷窗喷射氢气-空气混合物的自燃
International Journal of Hypersonics Pub Date : 2010-12-01 DOI: 10.1260/1759-3107.1.4.199
R. Kirchhartz, A. Paull, D. Mee, H. Olivier
{"title":"Self Ignition of Hydrogen-Air Mixtures with Inclined Porthole Injection in Supersonic Flows","authors":"R. Kirchhartz, A. Paull, D. Mee, H. Olivier","doi":"10.1260/1759-3107.1.4.199","DOIUrl":"https://doi.org/10.1260/1759-3107.1.4.199","url":null,"abstract":"Experiments were performed in the T4 shock tunnel to investigate the self ignition of hydrogen in a supersonic air stream. Hydrogen was injected into the flow over an inclined flat plate for oncoming Mach numbers of 7.9 to 8.0. The nozzle-supply enthalpy was kept between 3.1 and 3.4 MJ/kg and two different pressure levels were used in the tests. Measurements of surface pressures were used to infer the location of ignition but only small pressure increases were obtained when combustion occurred. Therefore multiple tests at nominally the same condition were used so that statistical methods could be used to identify the ignition lengths. The ignition lengths of the hydrogen air mixture directly behind a strong leading edge shock indicate that Pergament's method is able to predict the ignition length to within 35% for the observed autoignition over the range of conditions tested.","PeriodicalId":350070,"journal":{"name":"International Journal of Hypersonics","volume":"44 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123325415","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
引用次数: 0
Modeling of Plasma Assisted Combustion in Premixed Supersonic Gas Flow 预混合超声速气流中等离子体辅助燃烧的模拟
International Journal of Hypersonics Pub Date : 2010-12-01 DOI: 10.1260/1759-3107.1.4.209
M. Deminsky, I. Kochetov, A. Napartovich, S. Leonov
{"title":"Modeling of Plasma Assisted Combustion in Premixed Supersonic Gas Flow","authors":"M. Deminsky, I. Kochetov, A. Napartovich, S. Leonov","doi":"10.1260/1759-3107.1.4.209","DOIUrl":"https://doi.org/10.1260/1759-3107.1.4.209","url":null,"abstract":"A model for plasma assisted combustion of ethylene-air mixtures at conditions typical for scramjet combustion chamber is developed combining classical mechanisms of thermal combustion with non-thermal plasma chemistry. Numerical simulations showed that sufficiently strong reduction of ignition induction time at a reasonable energy cost can be realized with help of filamentary discharges. Starting from the discharge region, the gas mixture is heated due to exothermic reactions involving atomic oxygen and secondary chemical radicals. Temperature increment to the end of this stage for ethylene-air mixture is relatively small. An important effect of this stage is not heating but production of transient species. Then, a period with slow growth of temperature follows, which terminates by fast combustion. Processes causing the first fast growth of gas temperature are analyzed, and intermediate species controlling acceleration of ignition are determined numerically for plasma assisted combustion of stoichiometric mixture of ethylene with air. The value of the calculated induction time defined as a moment of the fast combustion is rather sensitive to the particular combustion mechanism adopted. This manifests a necessity to refine combustion mechanisms for conditions typical for scramjet combustion chamber with plasma initiation ‐ one atmosphere pressure, static gas temperature around 700 K and appearance of atomic oxygen † .","PeriodicalId":350070,"journal":{"name":"International Journal of Hypersonics","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122459125","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
引用次数: 14
Investigations on Sonic Normal and Oblique Jets in Hypersonic Cross-Flow 高超声速横流中正向和斜向射流的研究
International Journal of Hypersonics Pub Date : 2010-12-01 DOI: 10.1260/1759-3107.1.4.245
R. Joarder, G. Jagadeesh
{"title":"Investigations on Sonic Normal and Oblique Jets in Hypersonic Cross-Flow","authors":"R. Joarder, G. Jagadeesh","doi":"10.1260/1759-3107.1.4.245","DOIUrl":"https://doi.org/10.1260/1759-3107.1.4.245","url":null,"abstract":"This paper presents the results of numerical and experimental investigations on sonic jet (nitrogen) injections into a hypersonic cross-flow of air. The simulations aim at finding suitable injection conditions consistent with the experimental facility at IISc from the viewpoint of combustion. Numerical results under predicted the measured jet penetration depth for normal injection. It is found from numerical simulations that the total pressure loss in case of oblique injection is less than the normal injection.","PeriodicalId":350070,"journal":{"name":"International Journal of Hypersonics","volume":"9 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125696563","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
引用次数: 0
Experimental Investigation of the Effects of Aerospike Geometry on Aerodynamic Drag and Heat Transfer Rates for a Blunt Body Configuration at Hypersonic Mach Numbers 高超声速马赫数下钝体构型气动阻力和换热率影响气动刺几何形状的实验研究
International Journal of Hypersonics Pub Date : 2010-11-03 DOI: 10.1260/1759-3107.1.2.93
S. Srinath, K. Reddy
{"title":"Experimental Investigation of the Effects of Aerospike Geometry on Aerodynamic Drag and Heat Transfer Rates for a Blunt Body Configuration at Hypersonic Mach Numbers","authors":"S. Srinath, K. Reddy","doi":"10.1260/1759-3107.1.2.93","DOIUrl":"https://doi.org/10.1260/1759-3107.1.2.93","url":null,"abstract":"The effects of aerospike geometry on the drag reduction and heat transfer rates for a large-angle blunt cone flying at hypersonic Mach numbers are investigated in a hypersonic shock tunnel. Two spike geometries are considered. The first is a plain spike with a conical tip and the second is a telescopic aerospike fitted with discs of decreasing diameter in the direction opposite to the flow direction. These aerospikes are fitted to a 120° apex-angle blunt cone and results are investigated at free stream Mach numbers of 5.75 and 7.9 for different angles of attack. The aerodynamic forces are measured using an accelerometer-based force balance system and the heat transfer rates are measured using platinum thin film sensors. It is found that the telescopic aerospike has better drag reduction performance at angles of attack beyond 2° while the performance of the plain aerospike is better for angles of attack closer to zero degrees.","PeriodicalId":350070,"journal":{"name":"International Journal of Hypersonics","volume":"385 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-11-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"117303333","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
引用次数: 14
CFD Analysis of the Aerodynamic Interaction Effects Due to Lateral Jet Injection in to Hypersonic Flow 高超声速流动中侧向喷射气动相互作用效应的CFD分析
International Journal of Hypersonics Pub Date : 2010-11-03 DOI: 10.1260/1759-3107.1.2.135
P. Srinivas, Rishi Sharma, D. Yadav, G. Murty
{"title":"CFD Analysis of the Aerodynamic Interaction Effects Due to Lateral Jet Injection in to Hypersonic Flow","authors":"P. Srinivas, Rishi Sharma, D. Yadav, G. Murty","doi":"10.1260/1759-3107.1.2.135","DOIUrl":"https://doi.org/10.1260/1759-3107.1.2.135","url":null,"abstract":"Reentry vehicle often uses reaction control system for providing necessary critical forces during reentry. The effect of lateral jet due to reaction control system on aerodynamic characteristics especially stability aspect of a reentry vehicle has been investigated .CFD analysis of the interaction of a lateral jet on Leeward side has been investigated on a reentry body with a circular sonic air jet injected normally in to hypersonic flow from the body surface. A systematic numerical analysis for a lateral jet interaction was performed at angles of attack 0, 2, 5, 8, and 10 degrees at free stream Mach number 8.1. The methodology has also be verified by comparing the pressure distribution at an angle of attack of 20 degrees with experimental data. The effect of lateral jet on aerodynamic characteristic has been studied by comparing the variation of aerodynamic characteristic along the length with and without lateral jet. The aerodynamic coefficients variation of aerodynamic characteristics along the axial l...","PeriodicalId":350070,"journal":{"name":"International Journal of Hypersonics","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-11-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133198461","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
引用次数: 2
Investigation of Heat-Flux in High Enthalpy Hypersonic Flow Over a Rearward-Facing Step 高焓高超声速后阶流的热通量研究
International Journal of Hypersonics Pub Date : 2010-11-03 DOI: 10.1260/1759-3107.1.2.115
D. Ramanath, S. Gai, A. Neely
{"title":"Investigation of Heat-Flux in High Enthalpy Hypersonic Flow Over a Rearward-Facing Step","authors":"D. Ramanath, S. Gai, A. Neely","doi":"10.1260/1759-3107.1.2.115","DOIUrl":"https://doi.org/10.1260/1759-3107.1.2.115","url":null,"abstract":"Hypersonic laminar flow past a rearward facing step has been numerically investigated using computational fluid dynamics (CFD). The flow parameters were : total specific enthalpy ho ≈7.6 MJ/kg; unit Reynolds number Re ≈1.82 × 106 1/m ; and Mach number M∞ ≈7.6. A detailed grid independent study has been carried out to investigate the sensitivity of the surface heat flux in the regions of separation and reattachment. The nature of the flow in the close vicinity of the step is particularly emphasised. The influence of real-gas effects such as the thermal and chemical non-equilibrium are studied using Park's two-temperature model and finite-rate chemistry models respectively. The numerical results are then compared with the available experimental data of surface heat flux measurements.","PeriodicalId":350070,"journal":{"name":"International Journal of Hypersonics","volume":"188 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-11-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123321113","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
引用次数: 2
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