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International Journal of Hypersonics最新文献

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Study on the Mechanism of Quasi-Detonation 准爆轰机理研究
International Journal of Hypersonics Pub Date : 2010-09-01 DOI: 10.1260/1759-3107.1.3.145
Yunfeng Liu, Zonglin Jiang
{"title":"Study on the Mechanism of Quasi-Detonation","authors":"Yunfeng Liu, Zonglin Jiang","doi":"10.1260/1759-3107.1.3.145","DOIUrl":"https://doi.org/10.1260/1759-3107.1.3.145","url":null,"abstract":"In this paper, the mechanism of detonation to quasi-detonation transition was theoretically discussed, a new physical model to simulate quasi-detonation was proposed, and one-dimensional numerical simulation was conducted. This study first demonstrates that the quasi-detonation is of thermal choking. If the conditions of thermal choking are satisfied by the chemical release of energy and some disturbances, the supersonic flow is then unable to accept the additional thermal energy, and the CJ detonation becomes the unstable quasi-detonation precipitately. The kinetic energy loss consumed by this transition process is first considered in this new physical model. The numerical results are in good agreement with previous experimental observations qualitatively, which demonstrates that the quasi-detonation model is physically correct and the study is fundamentally important for detonation and supersonic combustion research.","PeriodicalId":350070,"journal":{"name":"International Journal of Hypersonics","volume":"105 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116655384","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
Analysis of a Tomography Technique for a Scramjet Wind Tunnel 超燃冲压发动机风洞层析成像技术分析
International Journal of Hypersonics Pub Date : 2010-09-01 DOI: 10.1260/1759-3107.1.3.173
E. F. Martin, C. Goyne, G. Diskin
{"title":"Analysis of a Tomography Technique for a Scramjet Wind Tunnel","authors":"E. F. Martin, C. Goyne, G. Diskin","doi":"10.1260/1759-3107.1.3.173","DOIUrl":"https://doi.org/10.1260/1759-3107.1.3.173","url":null,"abstract":"An experimental activity is currently underway to develop a tunable diode laser absorption tomography (TDLAT) technique to measure flow properties in a supersonic combustion wind tunnel. The present study simulates the reconstruction of spectroscopic measurements to determine the effects of data collection geometry and ambient water vapor on reconstruction accuracy. The study also proposes a way to remove the effects of ambient water vapor absorption. Overall, results show that TDLAT data collection time can be significantly reduced while maintaining reconstruction accuracy by taking fewer projections with a high density of rays and by correcting for ambient water vapor absorption.","PeriodicalId":350070,"journal":{"name":"International Journal of Hypersonics","volume":"48 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129843282","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
Experimental and Numerical Investigation of a Non-Axisymmetric Strut Based Ejector 非轴对称支杆型引射器的实验与数值研究
International Journal of Hypersonics Pub Date : 2010-09-01 DOI: 10.1260/1759-3107.1.3.181
M. Balasubramanyam, D. Lineberry, C. P. Chen, D. Landrum
{"title":"Experimental and Numerical Investigation of a Non-Axisymmetric Strut Based Ejector","authors":"M. Balasubramanyam, D. Lineberry, C. P. Chen, D. Landrum","doi":"10.1260/1759-3107.1.3.181","DOIUrl":"https://doi.org/10.1260/1759-3107.1.3.181","url":null,"abstract":"Tests were performed in a non-axisymmetric, single nozzle, strut-based ejector to investigate mass flow entrainment, choking mechanisms and stream mixing as a function of primary (strut nozzle) to secondary (duct inlet) flow stagnation pressure ratio. Experimental results show a mass flow choke in the mixing duct rather than a traditional aerodynamic choke in the strut gap. The stream mixing length was constant for lower primary flow pressures, whereas mixing length varied with pressure at higher values. A companion numerical study was performed using Reynolds Averaged Navier-Stokes solutions to investigate several turbulence models. Based on both 2-D and 3-D simulation results, compressibility correction to conventional incompressible twoequation models was required for capturing the supersonic ejector mixing phenomena. The Baldwin-Lomax and the SST two-equation models were capable of capturing the essential flow features. Even with compressibility correction, the k-Σ model could not reproduce wall-domin...","PeriodicalId":350070,"journal":{"name":"International Journal of Hypersonics","volume":"9 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132569746","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
Numerical Simulation of Liquid Fueled SCRAMJET Combustor Flow Fields 液体燃料超燃冲压发动机燃烧室流场数值模拟
International Journal of Hypersonics Pub Date : 2010-04-21 DOI: 10.1260/1759-3107.1.1.13
D. Chakraborty
{"title":"Numerical Simulation of Liquid Fueled SCRAMJET Combustor Flow Fields","authors":"D. Chakraborty","doi":"10.1260/1759-3107.1.1.13","DOIUrl":"https://doi.org/10.1260/1759-3107.1.1.13","url":null,"abstract":"Numerical simulations were carried out for various reacting flow fields related to scramjet propulsion system using commercial CFD Software. Three-dimensional Navier stokes equations were solved along with the K-e turbulence model. Modeling of the turbulence chemistry interaction is done through infinitely fast rate chemical kinetics. The software was validated extensively by comparing different experimental conditions for scramjet combustor to find its error band and range of application. Good agreement between the experimental and computational values were obtained for the scramjet combustor flow field with strut, pylon and cavity injection system with both hydrogen and hydrocarbon fuel. The validated CFD tool was applied in the design exercise of flight-sized kerosene fuel scramjet combustor of a hypersonic airbreathing mission. Significant improvement of combustion efficiency and thrust could be achieved by relocating the fuel injection system through the analysis of various thermochemical variables i...","PeriodicalId":350070,"journal":{"name":"International Journal of Hypersonics","volume":"23 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-04-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124025687","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: 3
Counterflow Drag Reduction Studies for a Blunt Cone in High Enthalpy Flow 高焓流钝锥逆流减阻研究
International Journal of Hypersonics Pub Date : 2010-04-21 DOI: 10.1260/1759-3107.1.1.69
V. Kulkarni, K. Reddy
{"title":"Counterflow Drag Reduction Studies for a Blunt Cone in High Enthalpy Flow","authors":"V. Kulkarni, K. Reddy","doi":"10.1260/1759-3107.1.1.69","DOIUrl":"https://doi.org/10.1260/1759-3107.1.1.69","url":null,"abstract":"Drag reduction by counterflow supersonic jet for a 60-degree apex angle blunt cone in high enthalpy flow is investigated in a free piston driven hypersonic shock tunnel, HST3. For flow Mach number of 8 with specific flow enthalpy of 5 MJ/kg, it has been observed that the drag force decreases with increase in the ratio of supersonic jet total pressure to the freestream pitot pressure until the critical injection pressure ratio is reached. Maximum percentage drag reduction of 44 is measured at the critical injection pressure ratio of 22.36. Further increase in injection pressure ratio has reduced the percentage drag reduction. Experimentally obtained drag signals portray the change in nature of the flowfield, around the model, across the critical injection pressure ratio.","PeriodicalId":350070,"journal":{"name":"International Journal of Hypersonics","volume":"188 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-04-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124752682","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: 10
Numerical Methods to Determine Convective Heating Rates on Aerodynamic Surfaces 确定气动表面对流加热速率的数值方法
International Journal of Hypersonics Pub Date : 2010-04-21 DOI: 10.1260/1759-3107.1.1.1
Bharat Kawale, R. Peetala, N. Sahoo, V. Kulkarni
{"title":"Numerical Methods to Determine Convective Heating Rates on Aerodynamic Surfaces","authors":"Bharat Kawale, R. Peetala, N. Sahoo, V. Kulkarni","doi":"10.1260/1759-3107.1.1.1","DOIUrl":"https://doi.org/10.1260/1759-3107.1.1.1","url":null,"abstract":"The approach for the present work is to develop a one-dimensional heat conduction model to infer the surface heating rates from the temperature data. The temperature history is obtained from a nickel thin film sensor mounted on a quartz substrate during a supersonic flight test. Polynomial curve fitting with regression analysis and cubic spline methods are used to fit the temperature data. One-dimensional numerical schemes are developed to infer surface heating rates by using Duhamel's superposition integral. Since the temperature data are acquired for 10 s, the one-dimensional behavior of heat penetration might not be applicable for entire time scale. In order to include the lateral conduction of heat along the depth of substrate, finite-element analysis of a more realistic gauge-substrate system is carried out with commercial package ANSYS 11. With the inputs of surface heating rates predicted from Duhamel's superposition integral, the temperature history are then recovered at various depths of the subs...","PeriodicalId":350070,"journal":{"name":"International Journal of Hypersonics","volume":"89 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-04-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"113992191","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
Force Measurement Techniques for Hypersonic Flows in Shock Tunnels 激波隧道中高超声速流动的力测量技术
International Journal of Hypersonics Pub Date : 2010-04-21 DOI: 10.1260/1759-3107.1.1.31
N. Sahoo, K. Reddy
{"title":"Force Measurement Techniques for Hypersonic Flows in Shock Tunnels","authors":"N. Sahoo, K. Reddy","doi":"10.1260/1759-3107.1.1.31","DOIUrl":"https://doi.org/10.1260/1759-3107.1.1.31","url":null,"abstract":"Recent advances in hypersonic research activities have led to the development in ground based test facilities for simulating near-realistic flight conditions in the laboratory. Basic performance data such as drag, lift, thrust etc., are usually obtained from ground-based experimentation for physical understanding of the flow fields and subsequent prototype developments. Hypersonic flows are produced for a very short time in impulse facilities such as shock tunnels, free-piston shock tunnels and expansion tubes. The test times are in the order of few milliseconds in the shock tunnel and for the expansion tubes, it is still less (~50 μs). The force measurements in these facilities are very challenging due the need of fast response sensors and instrumentations. In this review paper, two force measurement techniques are discussed that are best suited for short duration facilities namely; accelerometer balance and stress-wave force balance system.","PeriodicalId":350070,"journal":{"name":"International Journal of Hypersonics","volume":"18 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-04-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131688721","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: 8
Measurement of Drag on a Scramjet Engine in a Shock Tunnel 激波隧道中超燃冲压发动机阻力测量
International Journal of Hypersonics Pub Date : 2010-04-21 DOI: 10.1260/1759-3107.1.1.59
K. Anbuselvan, V. Menezes, K. Kumar
{"title":"Measurement of Drag on a Scramjet Engine in a Shock Tunnel","authors":"K. Anbuselvan, V. Menezes, K. Kumar","doi":"10.1260/1759-3107.1.1.59","DOIUrl":"https://doi.org/10.1260/1759-3107.1.1.59","url":null,"abstract":"The net drag on a non-fuelled, internal compression, constant-area combustor scramjet engine was measured using a single-component accelerometer balance in a shock tunnel at a freestream Mach number of 8 and a flow total enthalpy of 1.35 MJ/kg. The flow fields of the model were simulated using a commercial CFD code in order to understand the aerodynamics of the engine and compare with the measured net drag co-efficient. Measured and computed values of the net drag co-efficient were found to be in a good agreement.","PeriodicalId":350070,"journal":{"name":"International Journal of Hypersonics","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-04-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115841744","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
Short Duration Propulsion Test and Evaluation (Hy-V) Program 短持续时间推进试验和评估(Hy-V)项目
International Journal of Hypersonics Pub Date : 2009-10-19 DOI: 10.1260/1759-3107.1.2.77
C. Goyne, D. Cresci, T. Fetterhoff, Arnold Afb
{"title":"Short Duration Propulsion Test and Evaluation (Hy-V) Program","authors":"C. Goyne, D. Cresci, T. Fetterhoff, Arnold Afb","doi":"10.1260/1759-3107.1.2.77","DOIUrl":"https://doi.org/10.1260/1759-3107.1.2.77","url":null,"abstract":"The Short Duration Propulsion Test and Evaluation (SDPTE) Program and the Hy-V Program have recently been combined with the aim of examining the influence of ground test facilities on scramjet performance. The combined program includes both research and educational activities that are being conducted by a consortium of university, industry and government participants. The objectives of the combined program are to; 1) Resolve ground testing issues related to the effects of test medium on dual-mode scramjet engine performance, 2) Resolve ground testing issues related to the duration of the test flow on dual-mode scramjet engine performance, and 3) Educate and motivate a new generation of aerospace engineers through student participation and research. This paper provides an overview and status of the combined program but focuses on objectives 1) and 2). The ground testing issues associated with these objectives are being examined using a range of facilities. These include a continuous-flow direct connect facility, a freejet blowdown facility and an impulse facility. By testing in a range of facilities, the effects of combustion generated test medium vitiates and test flow duration on the operation of two dual-mode scramjet flowpaths will be examined. The experiments will focus on flowpath operation at conditions equivalent to a flight Mach number of 5. However, some Mach 7 freejet testing will also take place. The program will conclude with a Mach 5 flight experiment of both scramjet flowpaths aboard a sounding rocket such that differences between ground and flight performance data can also be isolated.","PeriodicalId":350070,"journal":{"name":"International Journal of Hypersonics","volume":"161 2","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2009-10-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114017849","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: 13
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