Pub Date : 2017-06-30DOI: 10.15866/IREASE.V10I3.11530
A. F. Razaami, M. Zorkipli, H. Lai, M. Z. Abdullah, N. A. Razak
This paper reports on the result of wind tunnel test of a mechanical flapping wing undergoing pure flapping with elbow joint. The objective of this work is to investigate the effect of reduced frequency on the unsteady pressure distribution around a flapping wing cross section. A specially designed mechanical wing flapper with elbow joint was developed and tested. The data measured were the kinematics, airspeeds and pressure distribution around the outer wing cross section at three different reduced frequencies. The results revealed three distinct flow phenomena of attach flow, laminar separation bubble and dynamic stall occurring at the reduced frequencies tested. These flow characteristics are dependent on the instantaneous effective angle of attack of the wing during flapping.
{"title":"Unsteady Pressure Distribution of a Flapping Wing Undergoing Root Flapping Motion with Elbow Joint at Different Reduced Frequencies","authors":"A. F. Razaami, M. Zorkipli, H. Lai, M. Z. Abdullah, N. A. Razak","doi":"10.15866/IREASE.V10I3.11530","DOIUrl":"https://doi.org/10.15866/IREASE.V10I3.11530","url":null,"abstract":"This paper reports on the result of wind tunnel test of a mechanical flapping wing undergoing pure flapping with elbow joint. The objective of this work is to investigate the effect of reduced frequency on the unsteady pressure distribution around a flapping wing cross section. A specially designed mechanical wing flapper with elbow joint was developed and tested. The data measured were the kinematics, airspeeds and pressure distribution around the outer wing cross section at three different reduced frequencies. The results revealed three distinct flow phenomena of attach flow, laminar separation bubble and dynamic stall occurring at the reduced frequencies tested. These flow characteristics are dependent on the instantaneous effective angle of attack of the wing during flapping.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"64 1","pages":"105-113"},"PeriodicalIF":0.0,"publicationDate":"2017-06-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"77723035","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 : 2017-06-30DOI: 10.15866/IREASE.V10I3.12487
F. Ismagilov, N. Uzhegov, V. Vavilov, D. Gusakov
This paper examines various designs of high-voltage, high-speed permanent magnet generators for autonomous objects. Based on the electromagnetic and system analyses, the best suitable design concept is selected taking into account the fault-tolerance capability of the generator. Different design topologies are compared by adopting an analytical approach, confirmed by finite element method (FEM) calculations. The main parameters and materials of the selected generator are presented and discussed. An experimental pilot study of the high-speed, high-voltage generator is carried out to verify the results of the computer simulations.
{"title":"Design Aspects of a High-Speed High-Voltage PMSM for Aerospace Application","authors":"F. Ismagilov, N. Uzhegov, V. Vavilov, D. Gusakov","doi":"10.15866/IREASE.V10I3.12487","DOIUrl":"https://doi.org/10.15866/IREASE.V10I3.12487","url":null,"abstract":"This paper examines various designs of high-voltage, high-speed permanent magnet generators for autonomous objects. Based on the electromagnetic and system analyses, the best suitable design concept is selected taking into account the fault-tolerance capability of the generator. Different design topologies are compared by adopting an analytical approach, confirmed by finite element method (FEM) calculations. The main parameters and materials of the selected generator are presented and discussed. An experimental pilot study of the high-speed, high-voltage generator is carried out to verify the results of the computer simulations.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"30 1","pages":"122-130"},"PeriodicalIF":0.0,"publicationDate":"2017-06-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"91538719","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 : 2017-06-30DOI: 10.15866/IREASE.V10I3.12394
E. Ewang, A. Miyahara, Arifur R. Khan, K. Toyoda, M. Cho
This study presents the development and implementation of a photoelectron current measurement system on-board HORYU-IV satellite to take on-orbit measurements from conductive and insulator surfaces. The measurement system aims at providing critical information on photoelectron yield of materials widely used onboard spacecraft. HORYU-IV is the fourth satellites of the HORYU series developed at Kyushu Institute of Technology and it was piggy-back launched on-board H-IIA F30 rocket at an altitude of 575 km on February 17, 2016 (JST). The measurement system mainly consists of current-voltage amplifier circuits for AU, Kapton® and black Kapton® samples with gains of 1x, 3x and 1x amplification, respectively. In this article, the analysis of the on-orbit results is presented. The on-orbit results show that a photoelectron current of 2.9nA and 3.1nA was measured from black Kapton® sample at respective elevations of 70.7° and 71.1°. These results respectively correspond to a current density of 14.0μA/m2 and 18.0μA/m2 at 71.1°. This study also presents various ground-based tests results performed to verify and validate the effectiveness of the photoelectron current measurement system developed for space applications.
{"title":"Photoelectron Current Measurement in Low Earth Orbit Using a Lean Satellite, HORYU-IV","authors":"E. Ewang, A. Miyahara, Arifur R. Khan, K. Toyoda, M. Cho","doi":"10.15866/IREASE.V10I3.12394","DOIUrl":"https://doi.org/10.15866/IREASE.V10I3.12394","url":null,"abstract":"This study presents the development and implementation of a photoelectron current measurement system on-board HORYU-IV satellite to take on-orbit measurements from conductive and insulator surfaces. The measurement system aims at providing critical information on photoelectron yield of materials widely used onboard spacecraft. HORYU-IV is the fourth satellites of the HORYU series developed at Kyushu Institute of Technology and it was piggy-back launched on-board H-IIA F30 rocket at an altitude of 575 km on February 17, 2016 (JST). The measurement system mainly consists of current-voltage amplifier circuits for AU, Kapton® and black Kapton® samples with gains of 1x, 3x and 1x amplification, respectively. In this article, the analysis of the on-orbit results is presented. The on-orbit results show that a photoelectron current of 2.9nA and 3.1nA was measured from black Kapton® sample at respective elevations of 70.7° and 71.1°. These results respectively correspond to a current density of 14.0μA/m2 and 18.0μA/m2 at 71.1°. This study also presents various ground-based tests results performed to verify and validate the effectiveness of the photoelectron current measurement system developed for space applications.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"20 1","pages":"140-153"},"PeriodicalIF":0.0,"publicationDate":"2017-06-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"89138435","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 : 2017-06-30DOI: 10.15866/IREASE.V10I3.11894
Kaouter Labed, H. Fizazi, H. Mahi
Image analysis has a large interest in remote sensing, it is used for extract pertinent information, and the segmentation is found at the bottom of each analysis. Image segmentation is also considered as one of the most difficult, critical and essential tasks in image processing. It determines the quality of the final analysis result. Image segmentation can be viewed as an optimization problem, Meta heuristic optimization methods and in particular bio-inspired methods are very used in image segmentation, they can be applied to any mono or multiobjective optimization problem. In this paper we present a meta heuristic approach based on Cuckoo Search Algorithm (CSA) for the purpose of solving the problem of image segmentation in general and in particularly the satellite images segmentation.
{"title":"Application of Cuckoo Search Algorithm for Image Segmentation","authors":"Kaouter Labed, H. Fizazi, H. Mahi","doi":"10.15866/IREASE.V10I3.11894","DOIUrl":"https://doi.org/10.15866/IREASE.V10I3.11894","url":null,"abstract":"Image analysis has a large interest in remote sensing, it is used for extract pertinent information, and the segmentation is found at the bottom of each analysis. Image segmentation is also considered as one of the most difficult, critical and essential tasks in image processing. It determines the quality of the final analysis result. Image segmentation can be viewed as an optimization problem, Meta heuristic optimization methods and in particular bio-inspired methods are very used in image segmentation, they can be applied to any mono or multiobjective optimization problem. In this paper we present a meta heuristic approach based on Cuckoo Search Algorithm (CSA) for the purpose of solving the problem of image segmentation in general and in particularly the satellite images segmentation.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"19 1","pages":"154-159"},"PeriodicalIF":0.0,"publicationDate":"2017-06-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"79561352","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 : 2017-06-30DOI: 10.15866/IREASE.V10I3.12469
M. Fakir, S. Khatun
This paper presents a comparative study of the distribution of temperature in a long-wide, insulated-tip rectangular fin. The numerical analysis and comparison of 2-dimensional heat conduction problem have been performed using both finite element method (FEM) and differential quadrature method (DQM). The surface solutions in terms of temperature distribution and error have been presented for comparison using both the methods. In FEM, the elements were generated with equally spaced called conventional FEM (CFEM) and with non-equally spaced called optimum FEM (OFEM). In DQM, the generation of mesh are only with non-equally spaced, called optimum DQM (ODQM). The ambient temperature is considered 20°C. The average percentage errors for OFEM, CFEM and ODQM are respectively 3.77E-02, 1.16E-01 and 4.10E-02. The surface temperature distribution and error comparison reveal that OFEM results are better and more precise than ODQM and CFEM results which show its potentiality.
{"title":"Two-Dimensional Heat Transfer Through Long-Wide Insulated-Tip Thin Rectangular Fin: a Comparative Study","authors":"M. Fakir, S. Khatun","doi":"10.15866/IREASE.V10I3.12469","DOIUrl":"https://doi.org/10.15866/IREASE.V10I3.12469","url":null,"abstract":"This paper presents a comparative study of the distribution of temperature in a long-wide, insulated-tip rectangular fin. The numerical analysis and comparison of 2-dimensional heat conduction problem have been performed using both finite element method (FEM) and differential quadrature method (DQM). The surface solutions in terms of temperature distribution and error have been presented for comparison using both the methods. In FEM, the elements were generated with equally spaced called conventional FEM (CFEM) and with non-equally spaced called optimum FEM (OFEM). In DQM, the generation of mesh are only with non-equally spaced, called optimum DQM (ODQM). The ambient temperature is considered 20°C. The average percentage errors for OFEM, CFEM and ODQM are respectively 3.77E-02, 1.16E-01 and 4.10E-02. The surface temperature distribution and error comparison reveal that OFEM results are better and more precise than ODQM and CFEM results which show its potentiality.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"103 1","pages":"167-173"},"PeriodicalIF":0.0,"publicationDate":"2017-06-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"80710208","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 : 2017-06-30DOI: 10.15866/IREASE.V10I3.12342
A. Sedel'nikov, K. I. Potienko
There is viewed the problem of reduction of controllability of spacecraft due to increase of inertia moment of spacecraft during conducting of active control over microacceleration level on the operational stage. Additional fuel stores, which are necessary for realization of spacecraft orbital orientation, are estimated. Recommendations to reduce influence of the phenomenon on effective running of system for orientation and control of spacecraft motion are given.
{"title":"Analysis of Reduction of Controllability of Spacecraft During Conducting of Active Control Over Microaccelerations","authors":"A. Sedel'nikov, K. I. Potienko","doi":"10.15866/IREASE.V10I3.12342","DOIUrl":"https://doi.org/10.15866/IREASE.V10I3.12342","url":null,"abstract":"There is viewed the problem of reduction of controllability of spacecraft due to increase of inertia moment of spacecraft during conducting of active control over microacceleration level on the operational stage. Additional fuel stores, which are necessary for realization of spacecraft orbital orientation, are estimated. Recommendations to reduce influence of the phenomenon on effective running of system for orientation and control of spacecraft motion are given.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"93 1","pages":"160-166"},"PeriodicalIF":0.0,"publicationDate":"2017-06-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"83840941","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 : 2017-06-30DOI: 10.15866/irease.v10i3.11980
Sarah Gherdaoui, H. Fizazi
The search and detection of the different regions constituting an image is a problem of great complexity and the use of the approximation algorithms is inevitable. For this purpose, several algorithms have been applied. Among the latter, we are interested in bio-inspiration by hybridizing two algorithms: Artificial Immunity Systems (AIS) with Evolutionary Algorithms (AE) in order to benefit from the good codification of the immune systems and the variation of the operators of the evolutionary algorithms, ensuring that the entire population is the solution. The main interests of this hybridization are to minimize the size of the representation of the individuals and to accelerate the convergence.
{"title":"Hybrid Approach for the Detection of Regions of a Satellite Image","authors":"Sarah Gherdaoui, H. Fizazi","doi":"10.15866/irease.v10i3.11980","DOIUrl":"https://doi.org/10.15866/irease.v10i3.11980","url":null,"abstract":"The search and detection of the different regions constituting an image is a problem of great complexity and the use of the approximation algorithms is inevitable. For this purpose, several algorithms have been applied. Among the latter, we are interested in bio-inspiration by hybridizing two algorithms: Artificial Immunity Systems (AIS) with Evolutionary Algorithms (AE) in order to benefit from the good codification of the immune systems and the variation of the operators of the evolutionary algorithms, ensuring that the entire population is the solution. The main interests of this hybridization are to minimize the size of the representation of the individuals and to accelerate the convergence.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"43 1","pages":"114-121"},"PeriodicalIF":0.0,"publicationDate":"2017-06-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"76804992","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 : 2017-06-30DOI: 10.15866/IREASE.V10I3.12615
F. Ismagilov, V. Vavilov, V. Bekuzin, V. Ayguzina
The paper presents the experimental research of different slotless high-speed electrical machine topologies for integration into the auxiliary power unit gearless. It was shown that the 6-poles and 8-poles with the concentrated windings and the wound stator core are the most effective for aerospace industry. Based on the experimental and computer research of different slotless high-speed electrical machine topologies. It was found that for use in the gearless auxiliary power unit of modern and perspective aircrafts, the use of the 6-poles and 8-poles slotless high-speed electrical machines with concentrated windings and wound stator core is the most effective. This topology allows providing the sufficient rigidity of the slotless high-speed electrical machine stator core, the minimum length of the frontal part and the minimum weight and size parameters of the slotless high-speed electrical machine at the maximum efficiency. In addition, in this case, the slotless high-speed electrical machine windings have a high inductance, which leads to limit the magnitude of short circuit currents.
{"title":"Topology Evaluation of a Slotless High-Speed Electrical Machine with Stator Core Made of an Amorphous Alloy for the Aerospace Industry","authors":"F. Ismagilov, V. Vavilov, V. Bekuzin, V. Ayguzina","doi":"10.15866/IREASE.V10I3.12615","DOIUrl":"https://doi.org/10.15866/IREASE.V10I3.12615","url":null,"abstract":"The paper presents the experimental research of different slotless high-speed electrical machine topologies for integration into the auxiliary power unit gearless. It was shown that the 6-poles and 8-poles with the concentrated windings and the wound stator core are the most effective for aerospace industry. Based on the experimental and computer research of different slotless high-speed electrical machine topologies. It was found that for use in the gearless auxiliary power unit of modern and perspective aircrafts, the use of the 6-poles and 8-poles slotless high-speed electrical machines with concentrated windings and wound stator core is the most effective. This topology allows providing the sufficient rigidity of the slotless high-speed electrical machine stator core, the minimum length of the frontal part and the minimum weight and size parameters of the slotless high-speed electrical machine at the maximum efficiency. In addition, in this case, the slotless high-speed electrical machine windings have a high inductance, which leads to limit the magnitude of short circuit currents.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"1 1","pages":"131-139"},"PeriodicalIF":0.0,"publicationDate":"2017-06-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"75516178","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 : 2017-06-30DOI: 10.15866/IREASE.V10I3.12404
E. Valencia, Chengyuan Liu, D. Nalianda, Laskaridis Panagiotis, Iain Gray, Riti Singh
The growing global environmental awareness has motivated the search for more fuel-efficient aircraft propulsion systems. In this context, a configuration based on distributed propulsion with Boundary Layer Ingestion (BLI) has been found to present potential performance benefits. The concept has been documented and explored extensively during the last few years and various aerodynamic integration issues, such as: high levels of distortion and low intake pressure recovery; have been identified as factors that may be detrimental in realizing the technology full potential. Parametric and parallel compressor (PC) approaches have been used to assess the effect of these aerodynamic issues on propulsors fan performance. However, in the context of BLI, these tools are unable to assess the effects of combined radial and circumferential distortion that are present. In order to assess the combined distortion patterns and the effects of distortion at component and system levels, this study uses a novel method based on semi-empirical correlations denominated the Discretized Miller (DM) approach. This method was developed for BLI systems previously by the author, and it is now incorporated into the propulsor performance method to assess the effects of the combined radial and circumferential distortion patterns. The performance analysis, undertaken at a component and system level, aims to assess several propulsion architectures, using Thrust Specific Fuel Consumption (TSFC) as figure of merit. To define the suitability of the distributed propulsor array in this study, an airframe layout based on the N3-X aircraft concept and High Temperature Superconducting (HTS) electric motor capabilities were assumed. The key contribution of this study is to enable the introduction of the concept of thrust split between energy source and propulsion system in the system analysis, and thereby, allows the assessment of its effects on different propulsion system layouts, while considering the BLI induced distortion. The results obtained with this alternative performance method showed that BLI reduces the fan efficiency of a conventional fan by approximately 2%, whilst corroborating the TSFC trends observed in previous studies. The study also indicates that when sizing effects of propulsors and core-engines were neglected, a propulsion system configuration with 75% thrust split was found optimum.
{"title":"Methodology for the Assessment of Distributed Propulsion Configurations with Boundary Layer Ingestion Using the Discretized Miller Approach","authors":"E. Valencia, Chengyuan Liu, D. Nalianda, Laskaridis Panagiotis, Iain Gray, Riti Singh","doi":"10.15866/IREASE.V10I3.12404","DOIUrl":"https://doi.org/10.15866/IREASE.V10I3.12404","url":null,"abstract":"The growing global environmental awareness has motivated the search for more fuel-efficient aircraft propulsion systems. In this context, a configuration based on distributed propulsion with Boundary Layer Ingestion (BLI) has been found to present potential performance benefits. The concept has been documented and explored extensively during the last few years and various aerodynamic integration issues, such as: high levels of distortion and low intake pressure recovery; have been identified as factors that may be detrimental in realizing the technology full potential. Parametric and parallel compressor (PC) approaches have been used to assess the effect of these aerodynamic issues on propulsors fan performance. However, in the context of BLI, these tools are unable to assess the effects of combined radial and circumferential distortion that are present. In order to assess the combined distortion patterns and the effects of distortion at component and system levels, this study uses a novel method based on semi-empirical correlations denominated the Discretized Miller (DM) approach. This method was developed for BLI systems previously by the author, and it is now incorporated into the propulsor performance method to assess the effects of the combined radial and circumferential distortion patterns. The performance analysis, undertaken at a component and system level, aims to assess several propulsion architectures, using Thrust Specific Fuel Consumption (TSFC) as figure of merit. To define the suitability of the distributed propulsor array in this study, an airframe layout based on the N3-X aircraft concept and High Temperature Superconducting (HTS) electric motor capabilities were assumed. The key contribution of this study is to enable the introduction of the concept of thrust split between energy source and propulsion system in the system analysis, and thereby, allows the assessment of its effects on different propulsion system layouts, while considering the BLI induced distortion. The results obtained with this alternative performance method showed that BLI reduces the fan efficiency of a conventional fan by approximately 2%, whilst corroborating the TSFC trends observed in previous studies. The study also indicates that when sizing effects of propulsors and core-engines were neglected, a propulsion system configuration with 75% thrust split was found optimum.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"48 1","pages":"174-187"},"PeriodicalIF":0.0,"publicationDate":"2017-06-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"78153288","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.V10I2.11512
N. Ahmed
In the present study, the concept of forward facing flap mounted on a slender delta wing, originally proposed by Hurley is considered. The test model resulted in surfaces that deflected from the basic delta to form a simple X-configuration. With this configuration, force balance measurements were conducted at low speed in a low speed open circuit wind tunnel. The lift produced was found to be dependent on both the flap deflection angle and thickness. Overall, the results obtained are very promising as they show definitive trends in the lift performance improvement of the X-configuration over conventional base delta wing at low angles of attack.
{"title":"Forward Facing Flap for Delta Wing Performance Improvement","authors":"N. Ahmed","doi":"10.15866/IREASE.V10I2.11512","DOIUrl":"https://doi.org/10.15866/IREASE.V10I2.11512","url":null,"abstract":"In the present study, the concept of forward facing flap mounted on a slender delta wing, originally proposed by Hurley is considered. The test model resulted in surfaces that deflected from the basic delta to form a simple X-configuration. With this configuration, force balance measurements were conducted at low speed in a low speed open circuit wind tunnel. The lift produced was found to be dependent on both the flap deflection angle and thickness. Overall, the results obtained are very promising as they show definitive trends in the lift performance improvement of the X-configuration over conventional base delta wing at low angles of attack.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"40 1","pages":"90-95"},"PeriodicalIF":0.0,"publicationDate":"2017-04-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"87284976","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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