Pub Date : 2023-09-04DOI: 10.13111/2066-8201.2023.15.3.8
G. Stroe, M. Costea
This paper examines the analysis of meteorological observations concerning wind direction and intensity. These observations are typically found in regular weather reports, which play a crucial role in the safe arrival and departure of aircraft, and provide vital information about current conditions along airport runways. To ensure accuracy, the locations of wind sensors along runways must be specified in routine weather reports. Furthermore, reported wind information data should be linked to the specific sections of the runway for which the data are representative. In cases where wind observations are available from multiple tracks, the relevant track information should also be included in routine weather reports, alongside the corresponding wind data. For surface wind conditions, the observations included in the METAR reports should accurately represent the entire runway, and it is important to indicate the specific runway or runway sections to which the observations pertain.
{"title":"Analysis of Global Systems, Support Centers, and Weather Units Aviation","authors":"G. Stroe, M. Costea","doi":"10.13111/2066-8201.2023.15.3.8","DOIUrl":"https://doi.org/10.13111/2066-8201.2023.15.3.8","url":null,"abstract":"This paper examines the analysis of meteorological observations concerning wind direction and intensity. These observations are typically found in regular weather reports, which play a crucial role in the safe arrival and departure of aircraft, and provide vital information about current conditions along airport runways. To ensure accuracy, the locations of wind sensors along runways must be specified in routine weather reports. Furthermore, reported wind information data should be linked to the specific sections of the runway for which the data are representative. In cases where wind observations are available from multiple tracks, the relevant track information should also be included\u0000in routine weather reports, alongside the corresponding wind data. For surface wind conditions, the observations included in the METAR reports should accurately represent the entire runway, and it is important to indicate the specific runway or runway sections to which the observations pertain.","PeriodicalId":37556,"journal":{"name":"INCAS Bulletin","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-09-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"42267734","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 : 2023-09-04DOI: 10.13111/2066-8201.2023.15.3.7
A. Seeni
The objective of this work is to analyze the aerodynamic response of SARAS transport aircraft to a gust condition. A rigid airframe is assumed. The increments in load factors due to vertical gust are calculated for gust gradient distances varying from 30 to 350ft as per Federal Aviation Requirements (FAR) specifications. The variations in the angles of attack due to gust and airplane motion are also studied. This tuned discrete gust analysis includes the effects of unsteady aerodynamics. The analysis is performed considering the aircraft plunge degree of motion (tail-off). The effect of damping due to the tail contribution is also studied.
{"title":"Discrete gust response analysis of SARAS aircraft","authors":"A. Seeni","doi":"10.13111/2066-8201.2023.15.3.7","DOIUrl":"https://doi.org/10.13111/2066-8201.2023.15.3.7","url":null,"abstract":"The objective of this work is to analyze the aerodynamic response of SARAS transport aircraft to a gust condition. A rigid airframe is assumed. The increments in load factors due to vertical gust are calculated for gust gradient distances varying from 30 to 350ft as per Federal Aviation Requirements (FAR) specifications. The variations in the angles of attack due to gust and airplane motion are also studied. This tuned discrete gust analysis includes the effects of unsteady aerodynamics. The analysis is performed considering the aircraft plunge degree of motion (tail-off). The effect of damping due to the tail contribution is also studied.","PeriodicalId":37556,"journal":{"name":"INCAS Bulletin","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-09-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"44426077","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 : 2023-09-04DOI: 10.13111/2066-8201.2023.15.3.3
Maria Casapu, Michel Arrigoni, Ion Fuiorea Fuiorea
Composite materials, among them Carbon Fiber Reinforced Polymers (CFRP), have become a key material in structural applications for lightweight structures such as spacecraft and aircraft. CFRP can be found under various quality grades and their mechanical performances increase with their cost and quality grade. In order to limit the costs of the material without degrading technical performances, hybridization could be of interest. However, assessing the conservation of quality standards of hybridized CFRP is crucial. This paper investigates the off-axis mechanical response of ply-level hybrid carbon composites, with varying thickness and material quality. Two types of carbon fiber prepregs were combined in the same laminate using symmetric and asymmetric stacking sequences. Monotonic quasi-static off-axis tests were performed to evaluate the non-linear stress-strain behavior of the laminates, with Digital Image Correlation used to measure strain. The apparent elastic modulus and the in-plane shear modulus were evaluated from the tensile tests at three off-axis angles. The results indicate that the hybrid laminates exhibit higher failure stress levels compared to simple laminates, with an intermediate failure strain. Overall, this study provides insights into the off-axis mechanical behavior of ply-level hybrid carbon fiber composites, with potential applications in the design of composite structures.
{"title":"Off-axis response and shear characterization of unidirectional ply-level hybrid carbon-fiber-reinforced polymer materials","authors":"Maria Casapu, Michel Arrigoni, Ion Fuiorea Fuiorea","doi":"10.13111/2066-8201.2023.15.3.3","DOIUrl":"https://doi.org/10.13111/2066-8201.2023.15.3.3","url":null,"abstract":"Composite materials, among them Carbon Fiber Reinforced Polymers (CFRP), have become a key material in structural applications for lightweight structures such as spacecraft and aircraft.\u0000CFRP can be found under various quality grades and their mechanical performances increase with their cost and quality grade. In order to limit the costs of the material without degrading technical performances, hybridization could be of interest. However, assessing the conservation of quality standards of hybridized CFRP is crucial. This paper investigates the off-axis mechanical response of ply-level hybrid carbon composites, with varying thickness and material quality. Two types of carbon\u0000fiber prepregs were combined in the same laminate using symmetric and asymmetric stacking sequences. Monotonic quasi-static off-axis tests were performed to evaluate the non-linear stress-strain behavior of the laminates, with Digital Image Correlation used to measure strain. The apparent elastic modulus and the in-plane shear modulus were evaluated from the tensile tests at three off-axis angles.\u0000The results indicate that the hybrid laminates exhibit higher failure stress levels compared to simple laminates, with an intermediate failure strain. Overall, this study provides insights into the off-axis mechanical behavior of ply-level hybrid carbon fiber composites, with potential applications in the design of composite structures.","PeriodicalId":37556,"journal":{"name":"INCAS Bulletin","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-09-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"46915984","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 : 2023-06-09DOI: 10.13111/2066-8201.2022.15.2.12
I. Caprian, Ionut Valentin Lom, Iurie Caprian
For five years now, the world economy has been affected by various crisis phenomena, which are currently forming as a consequence of the pandemic crisis, followed by the energy crisis, and the military conflict between Russia and Ukraine. Inevitably, this economic cataclysm has some influence on the global aviation insurance market. The recovery process of the global airline industry can be considered /seen as a beneficial factor in this context. At the same time, it is necessary to take into account the existing risk factors in this field of economic activity. Among the most important areas of adjustment in the aviation insurance market are the consequences of the pandemic crisis, cyber risks and the impact of the military conflict between Russia and Ukraine.
{"title":"Aviation insurance industry in the global economic crisis","authors":"I. Caprian, Ionut Valentin Lom, Iurie Caprian","doi":"10.13111/2066-8201.2022.15.2.12","DOIUrl":"https://doi.org/10.13111/2066-8201.2022.15.2.12","url":null,"abstract":"For five years now, the world economy has been affected by various crisis phenomena, which are currently forming as a consequence of the pandemic crisis, followed by the energy crisis, and the military conflict between Russia and Ukraine. Inevitably, this economic cataclysm has some influence on the global aviation insurance market. The recovery process of the global airline industry can be considered /seen as a beneficial factor in this context. At the same time, it is necessary to take into account the existing risk factors in this field of economic activity. Among the most important areas of adjustment in the aviation insurance market are the consequences of the pandemic crisis, cyber risks and the impact of the military conflict between Russia and Ukraine.","PeriodicalId":37556,"journal":{"name":"INCAS Bulletin","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-06-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"44742784","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 : 2023-06-09DOI: 10.13111/2066-8201.2023.15.2.2
Anton Balaban, S. Berbente, Andrei Neamtu, G. Stroe, Emil Costea, I. Stefanescu, I. Andrei, Ionel Popescu
In this paper, uncertainty is included in the extended framework of global air traffic both through the action of the wind and through the incomplete determination of the aerodynamic coefficients and the inevitable imprecision involved in the execution of ATC instructions. In order to study the air conflict detection process in detail, the possibility of potential conflicts must be evaluated, considering the current state of the international airspace, and taking into account the uncertainty in calculating the future position of the aircraft. A mathematical model for predicting potential aerial conflicts is necessary for this objective. In a probabilistic framework, the mathematical model thus created could be either an empirical distribution of future aircraft positions in space or a dynamic model, such as a stochastic differential equation, that describes the movement of the aircraft and implicitly defines a distribution for the position’s future of the aircraft/ future aircraft positions. Based on the prediction model, aircraft flight safety matrices can be evaluated. The mathematical methods applied in the Detection and Resolution of Air Traffic Conflicts - CDR involve a wide range of fields, but also the appropriate modeling of physical systems such as airplanes, the codification of mathematical algorithms for conflict detection, as well as the properly applied procedures for resolving potential air conflicts.
{"title":"Case study of TCAS implementation in modern FMS","authors":"Anton Balaban, S. Berbente, Andrei Neamtu, G. Stroe, Emil Costea, I. Stefanescu, I. Andrei, Ionel Popescu","doi":"10.13111/2066-8201.2023.15.2.2","DOIUrl":"https://doi.org/10.13111/2066-8201.2023.15.2.2","url":null,"abstract":"In this paper, uncertainty is included in the extended framework of global air traffic both through the action of the wind and through the incomplete determination of the aerodynamic coefficients and the inevitable imprecision involved in the execution of ATC instructions. In order to\u0000study the air conflict detection process in detail, the possibility of potential conflicts must be evaluated, considering the current state of the international airspace, and taking into account the uncertainty in\u0000calculating the future position of the aircraft. A mathematical model for predicting potential aerial conflicts is necessary for this objective. In a probabilistic framework, the mathematical model thus created could be either an empirical distribution of future aircraft positions in space or a dynamic model, such as a stochastic differential equation, that describes the movement of the aircraft and implicitly defines a distribution for the position’s future of the aircraft/ future aircraft positions. Based\u0000on the prediction model, aircraft flight safety matrices can be evaluated. The mathematical methods applied in the Detection and Resolution of Air Traffic Conflicts - CDR involve a wide range of fields, but also the appropriate modeling of physical systems such as airplanes, the codification of mathematical algorithms for conflict detection, as well as the properly applied procedures for resolving potential air conflicts.","PeriodicalId":37556,"journal":{"name":"INCAS Bulletin","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-06-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"47520287","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 : 2023-06-09DOI: 10.13111/2066-8201.2023.15.2.4
S. Haif, H. Kbab, Amina Benkhedda
Altitude-adapted nozzles are designed to facilitate flow adaptation during rocket ascent in the atmosphere, without requiring mechanical activation. As a consequence, the performance of the nozzle is significantly improved. The aim of this study is to develop a new profile of axisymmetric supersonic nozzles adapted at altitude (Dual Bell Nozzle with Central Body), which is characterized by an E-D nozzle as a basic profile. The performances obtained for this nozzle (E-D Nozzle) are then compared to those of a Plug nozzle. The E-D nozzle shows significant performance advantages over the Plug nozzle, including a 13.02% increase in thrust, knowing that the length of the E-D nozzle is half that of the Plug nozzle under the same design conditions. Finally, viscous calculations using the k-ω SST turbulence model were conducted to compare the performance of the dual bell nozzle with central body (DBNCB) and the E-D nozzle with the same cross-sectional ratio, and to assess the impact of nozzle pressure ratio (NPR) variations on the operation mode of the DBNCB. The results obtained show that the DBNCB offers the best performance in most phases of flight.
{"title":"Altitude-compensating axisymmetric supersonic nozzle design and flow analysis","authors":"S. Haif, H. Kbab, Amina Benkhedda","doi":"10.13111/2066-8201.2023.15.2.4","DOIUrl":"https://doi.org/10.13111/2066-8201.2023.15.2.4","url":null,"abstract":"Altitude-adapted nozzles are designed to facilitate flow adaptation during rocket ascent in the atmosphere, without requiring mechanical activation. As a consequence, the performance of the nozzle is significantly improved. The aim of this study is to develop a new profile of axisymmetric supersonic nozzles adapted at altitude (Dual Bell Nozzle with Central Body), which is characterized by an E-D nozzle as a basic profile. The performances obtained for this nozzle (E-D Nozzle) are then\u0000compared to those of a Plug nozzle. The E-D nozzle shows significant performance advantages over the Plug nozzle, including a 13.02% increase in thrust, knowing that the length of the E-D nozzle is half\u0000that of the Plug nozzle under the same design conditions. Finally, viscous calculations using the k-ω SST turbulence model were conducted to compare the performance of the dual bell nozzle with central body (DBNCB) and the E-D nozzle with the same cross-sectional ratio, and to assess the impact of nozzle pressure ratio (NPR) variations on the operation mode of the DBNCB. The results obtained show that the DBNCB offers the best performance in most phases of flight.","PeriodicalId":37556,"journal":{"name":"INCAS Bulletin","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-06-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"47306440","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 : 2023-06-09DOI: 10.13111/2066-8201.2023.15.2.14
I. RAMU, Battina N. MALLESWARARAO, J. CHANDRA SEKHAR, M. VENU, P. SENTHIL KUMAR
The present work aims to develop a computational procedure for investigating the vibration behaviour of pre-twisted laminated composite shell containing graphene inclusions in their matrix. According to nanoscopic empirical equations, graphene's mechanical properties are determined by its size dependence. It has been demonstrated that the orthotropic mechanical properties of composite laminates made from carbon fibres and hybrid matrix can be evaluated. Based on pre-twist and geometric configurations, finite element methods have been used to model hybrid materials shells that include carbon fibre, graphene, and graphene-fibre reinforcement. As part of the validation process, the proposed method is compared with other methods when possible. Finally, the vibrational behaviour of the composite shell is extracted by imposing a twisted angle on a cantilever boundary condition. An analysis of vibrations for each configuration is presented in this paper, as well as the effects of graphene inclusions on natural frequencies. As graphene volume fractions in the matrix increase, the natural frequencies of every mode also increase. When the hub radius and rotational speed are increased, the frequency parameter increases with an increase in graphene volume in the hybrid polymer composite pre-twisted shell.
{"title":"Study on Free Vibration Analysis of a Rotating Fibre-Graphene-Reinforced Hybrid Polymer Composites Pre-Twist Shel","authors":"I. RAMU, Battina N. MALLESWARARAO, J. CHANDRA SEKHAR, M. VENU, P. SENTHIL KUMAR","doi":"10.13111/2066-8201.2023.15.2.14","DOIUrl":"https://doi.org/10.13111/2066-8201.2023.15.2.14","url":null,"abstract":"The present work aims to develop a computational procedure for investigating the vibration behaviour of pre-twisted laminated composite shell containing graphene inclusions in their matrix. According to nanoscopic empirical equations, graphene's mechanical properties are determined by its size dependence. It has been demonstrated that the orthotropic mechanical properties of composite laminates made from carbon fibres and hybrid matrix can be evaluated. Based on pre-twist and geometric configurations, finite element methods have been used to model hybrid materials shells that include carbon fibre, graphene, and graphene-fibre reinforcement. As part of the validation process, the proposed method is compared with other methods when possible. Finally, the vibrational behaviour of the composite shell is extracted by imposing a twisted angle on a cantilever boundary condition. An analysis of vibrations for each configuration is presented in this paper, as well as the effects of graphene inclusions on natural frequencies. As graphene volume fractions in the matrix increase, the natural frequencies of every mode also increase. When the hub radius and rotational speed are increased, the frequency parameter increases with an increase in graphene volume in the hybrid polymer composite pre-twisted shell.","PeriodicalId":37556,"journal":{"name":"INCAS Bulletin","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-06-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135100726","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 : 2023-06-09DOI: 10.13111/2066-8201.2023.15.2.8
Seyi F. Olatoyinbo
A high-order computational fluid dynamics (CFD) code capable of solving compressible turbulent flow problems was developed. The CFD code employs the Flowfield Dependent Variation (FDV) scheme implemented in a Finite Element Method (FEM) framework. The FDV scheme is basically derived from the Lax-Wendroff Scheme (LWS) involving the replacement of LWS’s explicit time derivatives with a weighted combination of explicit and implicit time derivatives. The code utilizes linear, quadratic and cubic isoparametric quadrilateral and hexahedral Lagrange finite elements with corresponding piecewise shape functions that have formal spatial accuracy of second-order, third-order and fourth-order, respectively. In this paper, the results of observed order-of-accuracy of the implemented FDV FEM-based CFD code involving grid and polynomial order refinements on uniform Cartesian grids are reported. The Method of Manufactured Solutions (MMS) is applied to governing 2-D Euler and Navier-Stokes equations for flow cases spanning both subsonic and supersonic flow regimes. Global discretization error analyses using discrete 𝐿2 norm show that the spatial order-of-accuracy of the FDV FEM-based CFD code converges to the shape function polynomial order plus one, in excellent agreement with theory. Uniquely, this procedure establishes the wider applicability of MMS in verifying the spatial accuracy of a high-order CFD code.
{"title":"Verification of a High-Order FEM-based CFD Code using the Method of Manufactured Solutions","authors":"Seyi F. Olatoyinbo","doi":"10.13111/2066-8201.2023.15.2.8","DOIUrl":"https://doi.org/10.13111/2066-8201.2023.15.2.8","url":null,"abstract":"A high-order computational fluid dynamics (CFD) code capable of solving compressible turbulent flow problems was developed. The CFD code employs the Flowfield Dependent Variation (FDV) scheme implemented in a Finite Element Method (FEM) framework. The FDV scheme is basically derived from the Lax-Wendroff Scheme (LWS) involving the replacement of LWS’s explicit time derivatives with a weighted combination of explicit and implicit time derivatives. The code utilizes linear, quadratic and cubic isoparametric quadrilateral and hexahedral Lagrange finite elements with\u0000corresponding piecewise shape functions that have formal spatial accuracy of second-order, third-order and fourth-order, respectively. In this paper, the results of observed order-of-accuracy of the implemented FDV FEM-based CFD code involving grid and polynomial order refinements on uniform Cartesian grids are reported. The Method of Manufactured Solutions (MMS) is applied to governing 2-D Euler and Navier-Stokes equations for flow cases spanning both subsonic and supersonic flow regimes. Global discretization error analyses using discrete 𝐿2 norm show that the spatial order-of-accuracy of the FDV FEM-based CFD code converges to the shape function polynomial order plus one, in excellent agreement with theory. Uniquely, this procedure establishes the wider applicability of MMS in verifying the spatial accuracy of a high-order CFD code.","PeriodicalId":37556,"journal":{"name":"INCAS Bulletin","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-06-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"43822866","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 : 2023-06-09DOI: 10.13111/2066-8201.2023.15.2.10
Aravind SEENI
In an continuation of work previously performed by the author on grooved propellers, numerical investigations are performed on Applied Precision Composites 10×7 Slow Flyer propeller. Computational Fluid Dynamics is used to analyze the novel design. The grooved sections considered have a rectangular geometry measuring 0.1×0.1mm are placed interchangeably at 0.09c, 0.17c, 0.32c and 0.42c from the leading edge in a multi-grooved configuration i.e. more than 2 grooves. The results of the study showed that the presence of grooves had modified the flow characteristics only to detrimentally impact the thrust performance. However, the grooves improved power performance due to torque reduction. The analysis of the results showed that, in most models, low torque relative to the baseline in the operational range of the low to medium advance ratio range exists. The improvement in torque, however, did not improve efficiency in all models.
{"title":"Effect of Multiple Grooves on Aerodynamic Performance of a Low Reynolds Number UAV Propeller (Part II)","authors":"Aravind SEENI","doi":"10.13111/2066-8201.2023.15.2.10","DOIUrl":"https://doi.org/10.13111/2066-8201.2023.15.2.10","url":null,"abstract":"In an continuation of work previously performed by the author on grooved propellers, numerical investigations are performed on Applied Precision Composites 10×7 Slow Flyer propeller. Computational Fluid Dynamics is used to analyze the novel design. The grooved sections considered have a rectangular geometry measuring 0.1×0.1mm are placed interchangeably at 0.09c, 0.17c, 0.32c and 0.42c from the leading edge in a multi-grooved configuration i.e. more than 2 grooves. The results of the study showed that the presence of grooves had modified the flow characteristics only to detrimentally impact the thrust performance. However, the grooves improved power performance due to torque reduction. The analysis of the results showed that, in most models, low torque relative to the baseline in the operational range of the low to medium advance ratio range exists. The improvement in torque, however, did not improve efficiency in all models.","PeriodicalId":37556,"journal":{"name":"INCAS Bulletin","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-06-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135100735","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 : 2023-06-09DOI: 10.13111/2066-8201.2023.15.2.1
Anton BALABAN, Andrei NEAMTU, Sorin BERBENTE, Gabriela-Liliana STROE, Irina-Beatrice STEFANESCU, Emil COSTEA, Irina-Carmen ANDREI, Ionel POPESCU
This study shows how to generate images and compose images in the modern simulator room by starting multiple work sessions running at the same time so that all active server stations and the station to connect to are continuously displayed. Each server handles specific functions of the simulation process and runs a dedicated software application for its specific functions. For a supervised flight simulator, the following functions need to have dedicated applications: 1) Flight Dynamics Simulation, 2) Graphical projection, 3) Cockpit and Flight instrumentation simulation and integration, 4) Supervisor station. Out of these functions, Graphical projections and Cockpit and Flight instrumentation and integration require the most computational resources. Simulators need to present the view from a cockpit which requires a field of view of at least 180 degrees. This requires at least three displays usually in the form of projectors. In legacy implementations due to computational bottlenecks, each projector needed a dedicated computer. Similarly, the Cockpit and Flight instrumentation simulation requires usually upwards of 100 flight instrument simulations and embedded processors to be managed. In legacy implementations, one computer is needed for each piloting station. In recent implementations due to the increased performance of multi-core processors, many of these functions can be handled by single computers: the flight dynamics simulation and graphical projection functions can currently be handled by a single computer, similarly, all Cockpit and Flight instrumentation simulation and integration can be handled by another computer. Thus, a minimum of three servers are required to ensure full functionality of supervised simulation using modern computing systems.
{"title":"Considerations regarding the composition of the cockpit view for a modern simulator","authors":"Anton BALABAN, Andrei NEAMTU, Sorin BERBENTE, Gabriela-Liliana STROE, Irina-Beatrice STEFANESCU, Emil COSTEA, Irina-Carmen ANDREI, Ionel POPESCU","doi":"10.13111/2066-8201.2023.15.2.1","DOIUrl":"https://doi.org/10.13111/2066-8201.2023.15.2.1","url":null,"abstract":"This study shows how to generate images and compose images in the modern simulator room by starting multiple work sessions running at the same time so that all active server stations and the station to connect to are continuously displayed. Each server handles specific functions of the simulation process and runs a dedicated software application for its specific functions. For a supervised flight simulator, the following functions need to have dedicated applications: 1) Flight Dynamics Simulation, 2) Graphical projection, 3) Cockpit and Flight instrumentation simulation and integration, 4) Supervisor station. Out of these functions, Graphical projections and Cockpit and Flight instrumentation and integration require the most computational resources. Simulators need to present the view from a cockpit which requires a field of view of at least 180 degrees. This requires at least three displays usually in the form of projectors. In legacy implementations due to computational bottlenecks, each projector needed a dedicated computer. Similarly, the Cockpit and Flight instrumentation simulation requires usually upwards of 100 flight instrument simulations and embedded processors to be managed. In legacy implementations, one computer is needed for each piloting station. In recent implementations due to the increased performance of multi-core processors, many of these functions can be handled by single computers: the flight dynamics simulation and graphical projection functions can currently be handled by a single computer, similarly, all Cockpit and Flight instrumentation simulation and integration can be handled by another computer. Thus, a minimum of three servers are required to ensure full functionality of supervised simulation using modern computing systems.","PeriodicalId":37556,"journal":{"name":"INCAS Bulletin","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-06-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135100780","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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