Pub Date : 2017-10-31DOI: 10.15866/IREASE.V10I5.12855
A. R. Zahari, F. I. Romli
The Space Race between the Soviet Union and the United States back in 1960s had propelled vast development of space technology. Although it was still nascent during that time, space technology had spurred the launch of the first human to outer space and eventually the first human to step on the Moon. Nevertheless, the much celebrated technology breakthrough in human spaceflight could not expand its benefit to society due to the dual nature of space projects. Unlike other forms of technology, spacecraft and rocketry remain to be highly confidential and special privilege of space faring nations particularly their space agencies. With receding funding growth to these space agencies especially after the end of the Space Race, this paper aims to explore the potential of commercial human spaceflight in modern days to rejuvenate the development of space technology and its challenges. The scope of this paper is limited to commercial and private initiatives of human spaceflight, but not government or space agency. Towards the end, this paper concludes that commercial human spaceflight particularly the suborbital spaceflight has the potential to develop space tourism, point-to-point transportation, science research, satellite deployment, remote sensing, education, technology demonstration and media promotion.
{"title":"Potential of Commercial Human Spaceflight","authors":"A. R. Zahari, F. I. Romli","doi":"10.15866/IREASE.V10I5.12855","DOIUrl":"https://doi.org/10.15866/IREASE.V10I5.12855","url":null,"abstract":"The Space Race between the Soviet Union and the United States back in 1960s had propelled vast development of space technology. Although it was still nascent during that time, space technology had spurred the launch of the first human to outer space and eventually the first human to step on the Moon. Nevertheless, the much celebrated technology breakthrough in human spaceflight could not expand its benefit to society due to the dual nature of space projects. Unlike other forms of technology, spacecraft and rocketry remain to be highly confidential and special privilege of space faring nations particularly their space agencies. With receding funding growth to these space agencies especially after the end of the Space Race, this paper aims to explore the potential of commercial human spaceflight in modern days to rejuvenate the development of space technology and its challenges. The scope of this paper is limited to commercial and private initiatives of human spaceflight, but not government or space agency. Towards the end, this paper concludes that commercial human spaceflight particularly the suborbital spaceflight has the potential to develop space tourism, point-to-point transportation, science research, satellite deployment, remote sensing, education, technology demonstration and media promotion.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"67 1","pages":"277-281"},"PeriodicalIF":0.0,"publicationDate":"2017-10-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"83457358","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}
Pub Date : 2017-10-31DOI: 10.15866/IREASE.V10I5.12893
V. V. Kozoderov, T. V. Kondranin, E. Dmitriev
Imaging spectrometers with hundreds of spectral channels in visible and infrared regions are designed by various companies to enhance the information content of the relevant hyperspectral imagery processing compared to common-used multispectral systems. We review some sources on this particular subject to show the priorities of the hyperspectral approach before the multispectral one in forest and agriculture applications. There is also a discussion about some results of the information products obtained by an imaging spectrometer produced in Russia for a test area, where the ground-based forest inventory map is available to compare the traditional approaches and the newly defined ones. The related applications concern the pattern recognition of forest classes with different species and age on the test area using the airborne hyperspectral imagery processing.
{"title":"Hyperspectral Remote Sensing Imagery Processing Focused on Forest Applications","authors":"V. V. Kozoderov, T. V. Kondranin, E. Dmitriev","doi":"10.15866/IREASE.V10I5.12893","DOIUrl":"https://doi.org/10.15866/IREASE.V10I5.12893","url":null,"abstract":"Imaging spectrometers with hundreds of spectral channels in visible and infrared regions are designed by various companies to enhance the information content of the relevant hyperspectral imagery processing compared to common-used multispectral systems. We review some sources on this particular subject to show the priorities of the hyperspectral approach before the multispectral one in forest and agriculture applications. There is also a discussion about some results of the information products obtained by an imaging spectrometer produced in Russia for a test area, where the ground-based forest inventory map is available to compare the traditional approaches and the newly defined ones. The related applications concern the pattern recognition of forest classes with different species and age on the test area using the airborne hyperspectral imagery processing.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"218 1","pages":"298-307"},"PeriodicalIF":0.0,"publicationDate":"2017-10-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"74652850","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}
Pub Date : 2017-10-31DOI: 10.15866/IREASE.V10I5.13233
Ashok Kuppusamy, Sugjoon Yoon
Every aircraft simulator must undergo a series of test items to get certified by regulatory authority. For flight training devices being certified under FAA part 60 guidelines for level 5 and above, the control loading system provides a natural feel to the pilot that is a must for fulfilling the objective tests. In this paper, the test results of hardware control loader have been compared with the SIMULINK second order mathematical model representing a spring mass damper system. The parameters considered when choosing a second order transfer function are natural frequency and damping ratio. Considering the damping in the system, the values are chosen in such a way that it matches the results of hardware control loader. Hence, the spring mass damper model is named as high-fidelity control inceptor which is under-damped. The step response, frequency response analysis and pole-zero map plot are made to verify the stability of the system. The mathematical model results have been proved with actual experiments.
{"title":"Design and Validation of a Control Loading System for FAA Level 5 Flight Training Device of Cirrus SR-20 Airplanes","authors":"Ashok Kuppusamy, Sugjoon Yoon","doi":"10.15866/IREASE.V10I5.13233","DOIUrl":"https://doi.org/10.15866/IREASE.V10I5.13233","url":null,"abstract":"Every aircraft simulator must undergo a series of test items to get certified by regulatory authority. For flight training devices being certified under FAA part 60 guidelines for level 5 and above, the control loading system provides a natural feel to the pilot that is a must for fulfilling the objective tests. In this paper, the test results of hardware control loader have been compared with the SIMULINK second order mathematical model representing a spring mass damper system. The parameters considered when choosing a second order transfer function are natural frequency and damping ratio. Considering the damping in the system, the values are chosen in such a way that it matches the results of hardware control loader. Hence, the spring mass damper model is named as high-fidelity control inceptor which is under-damped. The step response, frequency response analysis and pole-zero map plot are made to verify the stability of the system. The mathematical model results have been proved with actual experiments.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"3 1","pages":"289-297"},"PeriodicalIF":0.0,"publicationDate":"2017-10-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"86884474","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}
Pub Date : 2017-08-31DOI: 10.15866/IREASE.V10I4.12561
J. Kraus, M. Štumper
The objective of this paper is to analyze current state of helicopter emergency medical service, to name its issues and to propose the solutions. The paper firstly describes the current research work in the form of two major projects related to helicopter emergency medical service and then focusing on the current directions of development. Final part of the paper proposes some solutions for helicopter emergency medical service issues, emphasizing those regarding Point in Space procedures and low-level routes.
{"title":"Issues with Introducing Instrument Flights for Helicopter Emergency Medical Service","authors":"J. Kraus, M. Štumper","doi":"10.15866/IREASE.V10I4.12561","DOIUrl":"https://doi.org/10.15866/IREASE.V10I4.12561","url":null,"abstract":"The objective of this paper is to analyze current state of helicopter emergency medical service, to name its issues and to propose the solutions. The paper firstly describes the current research work in the form of two major projects related to helicopter emergency medical service and then focusing on the current directions of development. Final part of the paper proposes some solutions for helicopter emergency medical service issues, emphasizing those regarding Point in Space procedures and low-level routes.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"37 1","pages":"224-229"},"PeriodicalIF":0.0,"publicationDate":"2017-08-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"80941403","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}
Pub Date : 2017-08-31DOI: 10.15866/IREASE.V10I4.12636
J. Julian, R. F. Karim, B. Budiarso, Harinaldi Harinaldi
This paper focuses on reviewing various flow control methods which have been applied on a squareback model. In order to understand the several issues related to the real practice, this review starts from the explanation of the aerodynamics of the backward facing step and finally of the squareback model itself. The aim of this review is to provide a comprehensive source of information regarding flow control on a squareback model as well as the fundamentals of the aerodynamics understanding in the related objects, and also to put several factors involving this issue in order to guide future findings and inventions to be able to locate the problem more easily.
{"title":"Review: Flow Control on a Squareback Model","authors":"J. Julian, R. F. Karim, B. Budiarso, Harinaldi Harinaldi","doi":"10.15866/IREASE.V10I4.12636","DOIUrl":"https://doi.org/10.15866/IREASE.V10I4.12636","url":null,"abstract":"This paper focuses on reviewing various flow control methods which have been applied on a squareback model. In order to understand the several issues related to the real practice, this review starts from the explanation of the aerodynamics of the backward facing step and finally of the squareback model itself. The aim of this review is to provide a comprehensive source of information regarding flow control on a squareback model as well as the fundamentals of the aerodynamics understanding in the related objects, and also to put several factors involving this issue in order to guide future findings and inventions to be able to locate the problem more easily.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"24 1","pages":"230-239"},"PeriodicalIF":0.0,"publicationDate":"2017-08-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"73325001","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}
Pub Date : 2017-08-31DOI: 10.15866/IREASE.V10I4.13779
S. Meo
In this paper, a numerical tool is presented in the field of the computation of electrical unknown of an electrical machine, very suitable to solve non-symmetrical condition too by means of a very friendly computer evaluation. This software tool, written in MATLAB language, bases itself on a formulation of air-gap field distribution by means of the linear combinations of the most elementary components of m.m.f (in case of windings) or of flux density (in case of permanent magnets) called Window functions. Differently from the standard methods, that allow appreciable results only after laborious calculations and complicate mathematical approaches that consent to formulate the problem in convenient domain, the proposed technique approaches and solves any problem directly in the time domain. The other most important feature of this procedure is its easy implementation into a proper tool that allows a friendly utilisation both by non expert people and by specialists in design phase activity or during the computation of performances in transient operations or in test conditions. In the paper, this tool is proposed in order to solve three cases of electrical machines simulations: the results demonstrate the interesting performance of the proposed tool.
本文提出了一种计算电机电气未知量的数值工具，通过一种非常友好的计算机评价方法，也非常适合求解非对称条件。这个软件工具是用MATLAB语言编写的，它基于气隙场分布的公式，通过称为窗口函数的mm - m - f(在绕组情况下)或磁通密度(在永磁体情况下)的最基本分量的线性组合。与标准方法不同，标准方法需要经过艰苦的计算和复杂的数学方法才能在方便的域内表述问题，而该技术直接在时域内接近和解决任何问题。该程序的另一个最重要的特点是它很容易实现成一个适当的工具，允许非专业人员和专家在设计阶段活动或在瞬态操作或测试条件下的性能计算期间友好地使用。在本文中，提出了该工具，以解决三种情况下的电机仿真，结果证明了该工具的有趣的性能。
{"title":"MADES Tool for the Analysis and Design of Electrical Machines","authors":"S. Meo","doi":"10.15866/IREASE.V10I4.13779","DOIUrl":"https://doi.org/10.15866/IREASE.V10I4.13779","url":null,"abstract":"In this paper, a numerical tool is presented in the field of the computation of electrical unknown of an electrical machine, very suitable to solve non-symmetrical condition too by means of a very friendly computer evaluation. This software tool, written in MATLAB language, bases itself on a formulation of air-gap field distribution by means of the linear combinations of the most elementary components of m.m.f (in case of windings) or of flux density (in case of permanent magnets) called Window functions. Differently from the standard methods, that allow appreciable results only after laborious calculations and complicate mathematical approaches that consent to formulate the problem in convenient domain, the proposed technique approaches and solves any problem directly in the time domain. The other most important feature of this procedure is its easy implementation into a proper tool that allows a friendly utilisation both by non expert people and by specialists in design phase activity or during the computation of performances in transient operations or in test conditions. In the paper, this tool is proposed in order to solve three cases of electrical machines simulations: the results demonstrate the interesting performance of the proposed tool.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"84 1","pages":"240-249"},"PeriodicalIF":0.0,"publicationDate":"2017-08-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"77741105","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}
Pub Date : 2017-08-31DOI: 10.15866/IREASE.V10I4.11774
A. Alsahlani, T. Rahulan
High-altitude aircraft flying in the stratosphere (around 20-30 km altitude) can provide a useful platform for sensors to support a range of surveillance tasks. Flying at high altitudes comes with a number of challenges. The air at high altitudes is thin and can considerably impact on the generation of sufficient lift and thrust. Moreover, powering the aircraft by solar energy with the aim of long-term operation adds extra challenges such as power management and system requirements. Therefore, the balancing of the energy and mass is usually taken to initiate the design process. In this paper, an analytical approach has been developed to conceptually design a solar-powered aircraft operating for long endurance at high-altitude. The total mass of the aircraft was defined as the summation of all aircraft elements. Each element was represented as a fraction of the total mass or the required power. These fractions were obtained from existing data of similar solar powered high-altitude UAVs. Also, a study has been conducted to explore the influence of mission requirements such as the flight level, the geographic location and the start & end date of the mission on the main characteristics of the aircraft. The design approach proved its capability by producing acceptable results for the weight and the power of the aircraft elements. This approach facilitates exploring the possible design space for a given mission in which the optimal weight and its corresponding set of characteristics can be easily concluded. The study of the mission parameters shows that designing the aircraft for high altitude operations can lead to a heavier aircraft despite the harvested solar energy at higher altitude being higher. Also, it was shown that the required surface area for solar panels is less than that required to generate adequate lift forces due to low air density. The duration of the daylight hours along with the intensity of solar radiation has a marked influence on achieving the design objective.
{"title":"A Mathematical Model of a Conceptual Design Approach of High Altitude Solar Powered Unmanned Aerial Vehicles","authors":"A. Alsahlani, T. Rahulan","doi":"10.15866/IREASE.V10I4.11774","DOIUrl":"https://doi.org/10.15866/IREASE.V10I4.11774","url":null,"abstract":"High-altitude aircraft flying in the stratosphere (around 20-30 km altitude) can provide a useful platform for sensors to support a range of surveillance tasks. Flying at high altitudes comes with a number of challenges. The air at high altitudes is thin and can considerably impact on the generation of sufficient lift and thrust. Moreover, powering the aircraft by solar energy with the aim of long-term operation adds extra challenges such as power management and system requirements. Therefore, the balancing of the energy and mass is usually taken to initiate the design process. In this paper, an analytical approach has been developed to conceptually design a solar-powered aircraft operating for long endurance at high-altitude. The total mass of the aircraft was defined as the summation of all aircraft elements. Each element was represented as a fraction of the total mass or the required power. These fractions were obtained from existing data of similar solar powered high-altitude UAVs. Also, a study has been conducted to explore the influence of mission requirements such as the flight level, the geographic location and the start & end date of the mission on the main characteristics of the aircraft. The design approach proved its capability by producing acceptable results for the weight and the power of the aircraft elements. This approach facilitates exploring the possible design space for a given mission in which the optimal weight and its corresponding set of characteristics can be easily concluded. The study of the mission parameters shows that designing the aircraft for high altitude operations can lead to a heavier aircraft despite the harvested solar energy at higher altitude being higher. Also, it was shown that the required surface area for solar panels is less than that required to generate adequate lift forces due to low air density. The duration of the daylight hours along with the intensity of solar radiation has a marked influence on achieving the design objective.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"25 1","pages":"196-206"},"PeriodicalIF":0.0,"publicationDate":"2017-08-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"80591689","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}
Pub Date : 2017-08-31DOI: 10.15866/IREASE.V10I4.12570
K. Ahmed, K. Bousson
The main purpose of this paper is to develop a trajectory optimization method to generate optimal trajectories that minimize aircraft total trip time between the initial and final waypoint in predefined 4D waypoint networks. In this paper, the 4D waypoint networks only consist of waypoints for climb, cruise and descent approach without the take-off and landing approach phases. The time optimal trajectory is generated for three different lengths of flights (short, medium, and long-haul flight) for two different commercial aircraft and considering zero wind condition. The Results about the presented applications show that by flying a time optimal trajectory, which was found by applying a single source shortest path algorithm (Dijkstra’s algorithm), can lead to the reduction of average travel time by 2.6% with respect to the total trip time.
{"title":"Generating Time Optimal Trajectory from Predefined 4D waypoint Networks","authors":"K. Ahmed, K. Bousson","doi":"10.15866/IREASE.V10I4.12570","DOIUrl":"https://doi.org/10.15866/IREASE.V10I4.12570","url":null,"abstract":"The main purpose of this paper is to develop a trajectory optimization method to generate optimal trajectories that minimize aircraft total trip time between the initial and final waypoint in predefined 4D waypoint networks. In this paper, the 4D waypoint networks only consist of waypoints for climb, cruise and descent approach without the take-off and landing approach phases. The time optimal trajectory is generated for three different lengths of flights (short, medium, and long-haul flight) for two different commercial aircraft and considering zero wind condition. The Results about the presented applications show that by flying a time optimal trajectory, which was found by applying a single source shortest path algorithm (Dijkstra’s algorithm), can lead to the reduction of average travel time by 2.6% with respect to the total trip time.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"13 1","pages":"207-214"},"PeriodicalIF":0.0,"publicationDate":"2017-08-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"73007467","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}
Pub Date : 2017-08-31DOI: 10.15866/IREASE.V10I4.12844
F. Ismagilov, V. Vavilov, D. Gusakov, Nikolai Tarasov
This paper considers the advantages and disadvantages of using electric generators with high-coercivity permanent magnets and a tooth-coil winding as a power source in hybrid power plant systems. The requirements of such power generators are considered. In this paper, a special topology of an electric generator with high-coercivity permanent magnets with the use of an additional winding is proposed. The features of the proposed generator topology are shown and its mathematical description is given. For the study of electromagnetic processes, a computer simulation of the proposed generator was performed and the results of modeling were presented. To verify the calculated values of the generator and the results of computer simulation, an experimental study on a prototype of the proposed electric generator with high-coercive permanent magnets was carried out. The results of the experimental study showed high accuracy of computer simulation and numerical calculation.
{"title":"Permanent Magnet Generator with the Tooth-Coil Winding and Saturation Magnetization of the Magnetic Core","authors":"F. Ismagilov, V. Vavilov, D. Gusakov, Nikolai Tarasov","doi":"10.15866/IREASE.V10I4.12844","DOIUrl":"https://doi.org/10.15866/IREASE.V10I4.12844","url":null,"abstract":"This paper considers the advantages and disadvantages of using electric generators with high-coercivity permanent magnets and a tooth-coil winding as a power source in hybrid power plant systems. The requirements of such power generators are considered. In this paper, a special topology of an electric generator with high-coercivity permanent magnets with the use of an additional winding is proposed. The features of the proposed generator topology are shown and its mathematical description is given. For the study of electromagnetic processes, a computer simulation of the proposed generator was performed and the results of modeling were presented. To verify the calculated values of the generator and the results of computer simulation, an experimental study on a prototype of the proposed electric generator with high-coercive permanent magnets was carried out. The results of the experimental study showed high accuracy of computer simulation and numerical calculation.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"13 1","pages":"250-258"},"PeriodicalIF":0.0,"publicationDate":"2017-08-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"73273829","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}
Pub Date : 2017-08-31DOI: 10.15866/IREASE.V10I4.12816
Shashank Khurana, Kojiro Suzuki, E. Rathakrishnan
Flow field around a cylindrical body with hemispherical nose, with and without spike was simulated in a water flow channel using water colour dyes at Froude number 6, utilizing Hydraulic analogy, equivalent to Mach 6 in gas flow, in a first-of-its-kind study. The prime focus in this work is on visualizing the formation of vortices near the stagnation area of the forebody, otherwise difficult in hypersonic wind tunnel experiments, together with observing key features distinctive to the water channel flow visualization technique. The effect of spike-nose configurations on the base region and flow field was also studied, together with discussion about observed peculiar flow features including the hydraulic jump. Two vortices of opposite family were observed on either side of the spike, with the largest for hemispherical-nose spike, closely corroborating with results from wind tunnel experiments and numerical simulations.
{"title":"Visualization of Vortex at Aero-Spike Root Using Hydraulic Analogy","authors":"Shashank Khurana, Kojiro Suzuki, E. Rathakrishnan","doi":"10.15866/IREASE.V10I4.12816","DOIUrl":"https://doi.org/10.15866/IREASE.V10I4.12816","url":null,"abstract":"Flow field around a cylindrical body with hemispherical nose, with and without spike was simulated in a water flow channel using water colour dyes at Froude number 6, utilizing Hydraulic analogy, equivalent to Mach 6 in gas flow, in a first-of-its-kind study. The prime focus in this work is on visualizing the formation of vortices near the stagnation area of the forebody, otherwise difficult in hypersonic wind tunnel experiments, together with observing key features distinctive to the water channel flow visualization technique. The effect of spike-nose configurations on the base region and flow field was also studied, together with discussion about observed peculiar flow features including the hydraulic jump. Two vortices of opposite family were observed on either side of the spike, with the largest for hemispherical-nose spike, closely corroborating with results from wind tunnel experiments and numerical simulations.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"17 1","pages":"189-195"},"PeriodicalIF":0.0,"publicationDate":"2017-08-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"89290072","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}
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