Pub Date : 2017-04-30DOI: 10.15866/IREASE.V10I2.11547
H. A. Kutty, P. Rajendran
This paper reviews the research conducted on propeller blades based on the performance evaluation method and available design. The review includes the propeller blades used for aircrafts, unmanned aerial vehicles, marine vehicles and wind turbines, as the working principle remain the same, differing only in operating conditions. Both experimental and numerical methods were discussed to provide a reliable procedure to investigate the performance of propeller blades. In addition, the propeller blades design was discussed, including conventional and unconventional blade designs. Blade shape, chord length and twist angle are the basic parameters for optimization method on conventional design. Optimization managed to improve propeller performance at an impressive rate. Many designs are currently being developed allowing more possibilities for blade design advancement.
{"title":"Review on Numerical and Experimental Research on Conventional and Unconventional Propeller Blade Design","authors":"H. A. Kutty, P. Rajendran","doi":"10.15866/IREASE.V10I2.11547","DOIUrl":"https://doi.org/10.15866/IREASE.V10I2.11547","url":null,"abstract":"This paper reviews the research conducted on propeller blades based on the performance evaluation method and available design. The review includes the propeller blades used for aircrafts, unmanned aerial vehicles, marine vehicles and wind turbines, as the working principle remain the same, differing only in operating conditions. Both experimental and numerical methods were discussed to provide a reliable procedure to investigate the performance of propeller blades. In addition, the propeller blades design was discussed, including conventional and unconventional blade designs. Blade shape, chord length and twist angle are the basic parameters for optimization method on conventional design. Optimization managed to improve propeller performance at an impressive rate. Many designs are currently being developed allowing more possibilities for blade design advancement.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"10 1","pages":"61-73"},"PeriodicalIF":0.0,"publicationDate":"2017-04-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"84213611","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 : 2017-04-30DOI: 10.15866/irease.v10i2.11873
Bachir Kaddar, H. Fizazi
NDVI time series has shown to be very efficient for vegetation change dynamic analysis over a long period. However, noise and illumination variations present significant challenges to perform an accurate change detection. This paper aims at capturing global vegetation change dynamics within 16-days MODIS-NDVI time series by considering the inter-annual variations. To determine the appropriate scale that characterizes the long term variation, an efficient way relying on wavelet transform is used. First, the Daubechies 4 wavelet transform is employed to perform a multi-scale decomposition to extract the inter-annual variations and remove noise. Second, critical point theory is used to identify a set of points indicating potential vegetation change within time series, which, allows a time series reduction. Then, for each critical point, LBP code is computed to characterize the corresponding local patterns, which provides the ability to deal with illumination variations. Based on the extracted features, a change map is produced by computing similarity between neighboring time series, assessing dynamic vegetation change over the period of study. Experiment results using NDVI time series show clearly the potential of the proposed approach to detect change.
{"title":"Spatiotemporal Analysis for NDVI Time Series Using Local Binary Pattern and Daubechies Wavelet Transform","authors":"Bachir Kaddar, H. Fizazi","doi":"10.15866/irease.v10i2.11873","DOIUrl":"https://doi.org/10.15866/irease.v10i2.11873","url":null,"abstract":"NDVI time series has shown to be very efficient for vegetation change dynamic analysis over a long period. However, noise and illumination variations present significant challenges to perform an accurate change detection. This paper aims at capturing global vegetation change dynamics within 16-days MODIS-NDVI time series by considering the inter-annual variations. To determine the appropriate scale that characterizes the long term variation, an efficient way relying on wavelet transform is used. First, the Daubechies 4 wavelet transform is employed to perform a multi-scale decomposition to extract the inter-annual variations and remove noise. Second, critical point theory is used to identify a set of points indicating potential vegetation change within time series, which, allows a time series reduction. Then, for each critical point, LBP code is computed to characterize the corresponding local patterns, which provides the ability to deal with illumination variations. Based on the extracted features, a change map is produced by computing similarity between neighboring time series, assessing dynamic vegetation change over the period of study. Experiment results using NDVI time series show clearly the potential of the proposed approach to detect change.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"112 1","pages":"96-104"},"PeriodicalIF":0.0,"publicationDate":"2017-04-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"88401185","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 : 2017-04-30DOI: 10.15866/IREASE.V10I2.12038
F. Ismagilov, V. Vavilov, N. Tarasov, V. Ayguzina
This paper presents the design and experimental research of a scaled-size prototype of the high-temperature starter-generator for more electric aircrafts. A computer model of the prototype with a high accuracy and good convergence with the experimental results was designed. In addition, the cooling efficiency evaluation was carried out; the losses in starter-generator active parts were estimated. Based on the results of experimental research and computer simulation, the full-size starter-generator was designed. It is important to notice that the full-size starter-generator was less loaded in terms of electromagnetic and thermal loads. This shows the proposed method efficiency. The obtained mass properties of the full-sized starter-generator is less than the 10 kg Thales’ starter-generator. This proves the efficiency of the researched variant.
{"title":"High-Temperature Starter-Generator with Fractional-Slot Concentrated Windings for More Electric Aircraft: Design and Testing of the Scaled-Size Prototype","authors":"F. Ismagilov, V. Vavilov, N. Tarasov, V. Ayguzina","doi":"10.15866/IREASE.V10I2.12038","DOIUrl":"https://doi.org/10.15866/IREASE.V10I2.12038","url":null,"abstract":"This paper presents the design and experimental research of a scaled-size prototype of the high-temperature starter-generator for more electric aircrafts. A computer model of the prototype with a high accuracy and good convergence with the experimental results was designed. In addition, the cooling efficiency evaluation was carried out; the losses in starter-generator active parts were estimated. Based on the results of experimental research and computer simulation, the full-size starter-generator was designed. It is important to notice that the full-size starter-generator was less loaded in terms of electromagnetic and thermal loads. This shows the proposed method efficiency. The obtained mass properties of the full-sized starter-generator is less than the 10 kg Thales’ starter-generator. This proves the efficiency of the researched variant.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"3 3 1","pages":"81-89"},"PeriodicalIF":0.0,"publicationDate":"2017-04-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"89657677","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 : 2017-04-30DOI: 10.15866/IREASE.V10I2.11708
F. Ismagilov, I. Khayrullin, V. Vavilov, V. Bekuzin, V. Ayguzina
{"title":"Increasing Energy Parameters of High-Speed Magneto-Electric Generator for Autonomous Objects","authors":"F. Ismagilov, I. Khayrullin, V. Vavilov, V. Bekuzin, V. Ayguzina","doi":"10.15866/IREASE.V10I2.11708","DOIUrl":"https://doi.org/10.15866/IREASE.V10I2.11708","url":null,"abstract":"","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"1 1","pages":"74"},"PeriodicalIF":0.0,"publicationDate":"2017-04-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"89682052","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 : 2017-04-30DOI: 10.15866/IREASE.V10I2.10593
F. Stesina, S. Corpino, L. Feruglio
The paper presents an end-to-end simulator aimed at supporting the engineering team in the design and verification activity across the whole product life cycle. The simulator is devoted to the analysis of small space systems, which present specific features if compared to large traditional platforms. Improving the understanding of the system early in the life cycle, and enhancing the verification process may help to increase the reliability and mission success of small-scale satellites while maintaining their key features of low cost and fast delivery. The simulator is designed through a Model and Simulation Based approach and allows performing "in-the-loop simulations" for the verification of functional and operational requirements at component, subsystem, and system level. The simulator is characterized by a modular architecture to adapt to several missions and different system configurations, also outside the space field. The core of the tool is a multi-processor workstation that sets up and runs the simulation, making use of a models database for the equipment and the mission environment, and a built-in interface unit to connect all the elements. The simulator has been successfully tested on a CubeSat project. Many test sessions were run and they are described into the detail in this article.
{"title":"In the loop simulator for the verification of small space platforms","authors":"F. Stesina, S. Corpino, L. Feruglio","doi":"10.15866/IREASE.V10I2.10593","DOIUrl":"https://doi.org/10.15866/IREASE.V10I2.10593","url":null,"abstract":"The paper presents an end-to-end simulator aimed at supporting the engineering team in the design and verification activity across the whole product life cycle. The simulator is devoted to the analysis of small space systems, which present specific features if compared to large traditional platforms. Improving the understanding of the system early in the life cycle, and enhancing the verification process may help to increase the reliability and mission success of small-scale satellites while maintaining their key features of low cost and fast delivery. The simulator is designed through a Model and Simulation Based approach and allows performing \"in-the-loop simulations\" for the verification of functional and operational requirements at component, subsystem, and system level. The simulator is characterized by a modular architecture to adapt to several missions and different system configurations, also outside the space field. The core of the tool is a multi-processor workstation that sets up and runs the simulation, making use of a models database for the equipment and the mission environment, and a built-in interface unit to connect all the elements. The simulator has been successfully tested on a CubeSat project. Many test sessions were run and they are described into the detail in this article.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"12 1","pages":"50"},"PeriodicalIF":0.0,"publicationDate":"2017-04-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"79154344","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 : 2017-02-28DOI: 10.15866/IREASE.V10I1.10501
C. Grillo, F. Montano
An innovative use of the Extended Kalman Filter (EKF) is proposed to perform both accurate path following and adequate disturbance rejection in turbulent air. The tuned up procedure employs simultaneously two different EKF: the first one estimates gust disturbances, the second one estimates modified aircraft parameters. The first filter, by using measurements gathered in turbulent air, estimates both aircraft states and wind components. The second one, by using the estimated disturbances, obtains command laws that are able to reject disturbances. The predictor of the second EKF uses the estimated wind components to solve motion equations in turbulent air. Besides a set of unknown stability and control parameters (containing displacements of the controls) is introduced into the predictor. This set contains modified aerodynamic coefficients. These ones are obtained by adding entirely new derivatives or synthetic increments to basic ones. Therefore, the above aforementioned unknown values of aircraft parameters augment the aircraft’s state. The filter estimates the augmented state by using a set of measurements formed by the desired flight path variables. In this way, it is possible to obtain the command laws by using the postulated unknown stability and control derivatives, which contain the control displacements. Therefore, the obtained control laws, related to either the characteristics of the disturbance or the desired flight path, are adaptive.
{"title":"An EKF Based Method for Path Following in Turbulent Air","authors":"C. Grillo, F. Montano","doi":"10.15866/IREASE.V10I1.10501","DOIUrl":"https://doi.org/10.15866/IREASE.V10I1.10501","url":null,"abstract":"An innovative use of the Extended Kalman Filter (EKF) is proposed to perform both accurate path following and adequate disturbance rejection in turbulent air. The tuned up procedure employs simultaneously two different EKF: the first one estimates gust disturbances, the second one estimates modified aircraft parameters. The first filter, by using measurements gathered in turbulent air, estimates both aircraft states and wind components. The second one, by using the estimated disturbances, obtains command laws that are able to reject disturbances. The predictor of the second EKF uses the estimated wind components to solve motion equations in turbulent air. Besides a set of unknown stability and control parameters (containing displacements of the controls) is introduced into the predictor. This set contains modified aerodynamic coefficients. These ones are obtained by adding entirely new derivatives or synthetic increments to basic ones. Therefore, the above aforementioned unknown values of aircraft parameters augment the aircraft’s state. The filter estimates the augmented state by using a set of measurements formed by the desired flight path variables. In this way, it is possible to obtain the command laws by using the postulated unknown stability and control derivatives, which contain the control displacements. Therefore, the obtained control laws, related to either the characteristics of the disturbance or the desired flight path, are adaptive.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"25 5 1","pages":"1-6"},"PeriodicalIF":0.0,"publicationDate":"2017-02-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"82692764","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 : 2017-02-28DOI: 10.15866/IREASE.V10I1.11034
V. Vavilov
The main purpose of this article is to perform experiments on a scaled model of the SG on HPS with permanent magnets, a teeth winding and an outer rotor at temperature of up to 2200С to analyze its electromechanical characteristics. On the basis of these researches, it is possible to create and verify the computer model in Ansys Maxwell which allows linear scaling of SG dimensions to design a SG with higher capacity. This paper also deals with the application efficiency research of different types of high-temperature wires (including copper conductor and nickel conductors). It helps to choose the best variant for the SG with HPS. Changings on losses in a high-temperature SG with a rise in temperature is analyzed as well. On the basis of research results the conclusion on practicality of the suggested concept and the SG structural design are given. The novelty of the paper is that the experimental research results of the high-temperature SG on HPS with a teeth winding and an outer rotor at a temperature of 2200С is being published for the first time. The conclusion on the integration of the SG into HPSs are being given based on the researches.
{"title":"Integrated High-Temperature Starter-Generator for Aerospace Vehicles. Testing of a Scaled-Size Prototype","authors":"V. Vavilov","doi":"10.15866/IREASE.V10I1.11034","DOIUrl":"https://doi.org/10.15866/IREASE.V10I1.11034","url":null,"abstract":"The main purpose of this article is to perform experiments on a scaled model of the SG on HPS with permanent magnets, a teeth winding and an outer rotor at temperature of up to 2200С to analyze its electromechanical characteristics. On the basis of these researches, it is possible to create and verify the computer model in Ansys Maxwell which allows linear scaling of SG dimensions to design a SG with higher capacity. This paper also deals with the application efficiency research of different types of high-temperature wires (including copper conductor and nickel conductors). It helps to choose the best variant for the SG with HPS. Changings on losses in a high-temperature SG with a rise in temperature is analyzed as well. On the basis of research results the conclusion on practicality of the suggested concept and the SG structural design are given. The novelty of the paper is that the experimental research results of the high-temperature SG on HPS with a teeth winding and an outer rotor at a temperature of 2200С is being published for the first time. The conclusion on the integration of the SG into HPSs are being given based on the researches.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"22 1","pages":"24-30"},"PeriodicalIF":0.0,"publicationDate":"2017-02-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"82020497","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 : 2017-02-28DOI: 10.15866/irease.v10i1.11191
Mustapha Si Tayeb, H. Fizazi
The traditional methods for extracting information from satellite images are generally based on the spectral response of the sensors. These approaches are in some cases insufficient in particular in case of high-resolution images. In fact these images have a spectral content increasingly heterogeneous. It is, therefore, necessary to use more efficient analysis methods. The multi-source classification is a robust analytical tool, and it is one of the most used approaches for the extraction of telemetric information. This paper is focused on the problem of the classification of satellite images by the hybridization of several methods: multi-layer perceptron, hidden Markov models and genetic algorithms. The results prove the efficiency of the proposed final approach, with a classification rate of 98.79%, significantly higher respect to the results obtained by the MLP method, and by other approaches.
{"title":"A Dual-Level Hybrid Approach for Classification of Satellite Images","authors":"Mustapha Si Tayeb, H. Fizazi","doi":"10.15866/irease.v10i1.11191","DOIUrl":"https://doi.org/10.15866/irease.v10i1.11191","url":null,"abstract":"The traditional methods for extracting information from satellite images are generally based on the spectral response of the sensors. These approaches are in some cases insufficient in particular in case of high-resolution images. In fact these images have a spectral content increasingly heterogeneous. It is, therefore, necessary to use more efficient analysis methods. The multi-source classification is a robust analytical tool, and it is one of the most used approaches for the extraction of telemetric information. This paper is focused on the problem of the classification of satellite images by the hybridization of several methods: multi-layer perceptron, hidden Markov models and genetic algorithms. The results prove the efficiency of the proposed final approach, with a classification rate of 98.79%, significantly higher respect to the results obtained by the MLP method, and by other approaches.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"18 1","pages":"42-49"},"PeriodicalIF":0.0,"publicationDate":"2017-02-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"81758271","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 : 2017-02-28DOI: 10.15866/IREASE.V10I1.10848
V. M. Kulkov, V. V. Terentyev, S. O. Firsyuk
In this paper, the problem of clearing up low-Earth orbit from the man-made space debris is considered. For this purpose the variants of released in space inflatable ballutes (IB) are proposed. A set of mathematical models and systems of equations, sufficient to evaluate the requirements for the design of the spacecraft equipped with IB, is formed. For an object with a low mass (about 20 kg, which corresponds to a small spacecraft) the calculation of the basic parameters for this orbit is carried out and the results for four different initial attitudes are shown. Finally the requirements for the design and characteristics of the IB materials are described.
{"title":"Justification Possibilities of Removing Man-Made Objects from the Earth's Orbit Using Inflatable Structures","authors":"V. M. Kulkov, V. V. Terentyev, S. O. Firsyuk","doi":"10.15866/IREASE.V10I1.10848","DOIUrl":"https://doi.org/10.15866/IREASE.V10I1.10848","url":null,"abstract":"In this paper, the problem of clearing up low-Earth orbit from the man-made space debris is considered. For this purpose the variants of released in space inflatable ballutes (IB) are proposed. A set of mathematical models and systems of equations, sufficient to evaluate the requirements for the design of the spacecraft equipped with IB, is formed. For an object with a low mass (about 20 kg, which corresponds to a small spacecraft) the calculation of the basic parameters for this orbit is carried out and the results for four different initial attitudes are shown. Finally the requirements for the design and characteristics of the IB materials are described.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"12 1","pages":"7-13"},"PeriodicalIF":0.0,"publicationDate":"2017-02-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"75428981","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 : 2017-02-28DOI: 10.15866/IREASE.V10I1.10491
A. J. Torres, R. Bardera-Mora, Mario Sánchez García, M. Calero
Backward-Facing Step (BFS) shape is a common configuration found in several engineering applications. The turbulent flow structure in the backside of a BFS leads to risky situations. Then, flow control is a useful technique to achieve safe conditions. In recent years, plasma devices have become an interesting technology with high importance for flow control because of non-moving parts, fast time response and low energy consumption. This paper presents the experimental investigation of a set of Dielectric Barrier Discharge (DBD) plasma actuators placed on the rounded edge of a BFS and its capability for flow control by wind tunnel testing. In contrast to the other studies, the behaviour of the plasma actuators in presence of 3D flow over a BFS was investigated. Firstly, a parametric study by analysing the location and the influence of the electrical parameters of the DBD plasma actuator was performed at a freestream velocity of 6 m/s using Particle Image Velocimetry (PIV). It was seen that actuator with -45° wall jet provides the highest flow control at 30 kVpp and 2.5 kHz with a reattachment length reduction of 65.6% referred to plasma off case. This configuration was optimized and compared with a double actuator for a higher velocity (10 m/s). The manufacturing complexity of the double actuator recommends the use of a simple actuator due to the fact that they have similar results, with a 30% of reattachment point reduction approximately at 10 m/s. Anyhow, the results confirm the authority of plasma actuators to modify the flow structure behind a BFS.
{"title":"3D Backward-Facing Step Flow Structure Modification with Plasma Actuators","authors":"A. J. Torres, R. Bardera-Mora, Mario Sánchez García, M. Calero","doi":"10.15866/IREASE.V10I1.10491","DOIUrl":"https://doi.org/10.15866/IREASE.V10I1.10491","url":null,"abstract":"Backward-Facing Step (BFS) shape is a common configuration found in several engineering applications. The turbulent flow structure in the backside of a BFS leads to risky situations. Then, flow control is a useful technique to achieve safe conditions. In recent years, plasma devices have become an interesting technology with high importance for flow control because of non-moving parts, fast time response and low energy consumption. This paper presents the experimental investigation of a set of Dielectric Barrier Discharge (DBD) plasma actuators placed on the rounded edge of a BFS and its capability for flow control by wind tunnel testing. In contrast to the other studies, the behaviour of the plasma actuators in presence of 3D flow over a BFS was investigated. Firstly, a parametric study by analysing the location and the influence of the electrical parameters of the DBD plasma actuator was performed at a freestream velocity of 6 m/s using Particle Image Velocimetry (PIV). It was seen that actuator with -45° wall jet provides the highest flow control at 30 kVpp and 2.5 kHz with a reattachment length reduction of 65.6% referred to plasma off case. This configuration was optimized and compared with a double actuator for a higher velocity (10 m/s). The manufacturing complexity of the double actuator recommends the use of a simple actuator due to the fact that they have similar results, with a 30% of reattachment point reduction approximately at 10 m/s. Anyhow, the results confirm the authority of plasma actuators to modify the flow structure behind a BFS.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"31 1","pages":"14-23"},"PeriodicalIF":0.0,"publicationDate":"2017-02-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"81245457","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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