Damage tolerance evaluation of wing in presence of large landing gear cutout ...eSAT Journals
Abstract Aircraft is symbol of a high performance mechanical structure, which has the ability to fly with a very high structural safety record. Aircraft experiences variable loading in service. Rarely an aircraft will fail due to a static overload during its service life. For the continued airworthiness of an aircraft during its entire economic service life, fatigue and damage tolerance design, analysis, testing and service experience correlation play a pivotal role. The present study includes the stress analysis and damage tolerance evaluation of the wing through a stiffened panel of the bottom skin with a landing gear cutout. Wing bottom skin experiences tensile stress field during flight. Cutouts required for fuel access and landing gear opening and retraction in the bottom skin will introduce stress concentration. Fatigue cracks will initiate from high tensile stress locations. An integral stiffened panel consisting a landing gear cutout is considered for the analysis. Stress analysis will identify the maximum tensile stress location in the panel. In a metallic structure fatigue manifests itself in the form of a crack which propagates. If the crack in a critical location goes unnoticed it could lead to a catastrophic failure of the airframe. A critical condition will occur when the stress intensity factor (SIF) at the crack tip becomes equal to fracture toughness of the material. SIF calculations will be carried out for a crack with incremental crack lengths using MVCCI method. Analytical evaluation of the crack arrest capability of the stiffening members ahead of the crack tip will be carried out. Index Terms: Key Aircraft, Design, wing, landing gear cutout, stress analysis, FEM, damage tolerance, integral stiffened panel.
Damage tolerance evaluation of wing in presence of large landing gear cutout ...eSAT Publishing House
IJRET : International Journal of Research in Engineering and Technology is an international peer reviewed, online journal published by eSAT Publishing House for the enhancement of research in various disciplines of Engineering and Technology. The aim and scope of the journal is to provide an academic medium and an important reference for the advancement and dissemination of research results that support high-level learning, teaching and research in the fields of Engineering and Technology. We bring together Scientists, Academician, Field Engineers, Scholars and Students of related fields of Engineering and Technology
International Journal of Engineering Research and Applications (IJERA) is a team of researchers not publication services or private publications running the journals for monetary benefits, we are association of scientists and academia who focus only on supporting authors who want to publish their work. The articles published in our journal can be accessed online, all the articles will be archived for real time access.
Our journal system primarily aims to bring out the research talent and the works done by sciaentists, academia, engineers, practitioners, scholars, post graduate students of engineering and science. This journal aims to cover the scientific research in a broader sense and not publishing a niche area of research facilitating researchers from various verticals to publish their papers. It is also aimed to provide a platform for the researchers to publish in a shorter of time, enabling them to continue further All articles published are freely available to scientific researchers in the Government agencies,educators and the general public. We are taking serious efforts to promote our journal across the globe in various ways, we are sure that our journal will act as a scientific platform for all researchers to publish their works online.
IJRET : International Journal of Research in Engineering and Technology is an international peer reviewed, online journal published by eSAT Publishing House for the enhancement of research in various disciplines of Engineering and Technology. The aim and scope of the journal is to provide an academic medium and an important reference for the advancement and dissemination of research results that support high-level learning, teaching and research in the fields of Engineering and Technology. We bring together Scientists, Academician, Field Engineers, Scholars and Students of related fields of Engineering and Technology.
Damage tolerance evaluation of wing in presence of large landing gear cutout ...eSAT Journals
Abstract Aircraft is symbol of a high performance mechanical structure, which has the ability to fly with a very high structural safety record. Aircraft experiences variable loading in service. Rarely an aircraft will fail due to a static overload during its service life. For the continued airworthiness of an aircraft during its entire economic service life, fatigue and damage tolerance design, analysis, testing and service experience correlation play a pivotal role. The present study includes the stress analysis and damage tolerance evaluation of the wing through a stiffened panel of the bottom skin with a landing gear cutout. Wing bottom skin experiences tensile stress field during flight. Cutouts required for fuel access and landing gear opening and retraction in the bottom skin will introduce stress concentration. Fatigue cracks will initiate from high tensile stress locations. An integral stiffened panel consisting a landing gear cutout is considered for the analysis. Stress analysis will identify the maximum tensile stress location in the panel. In a metallic structure fatigue manifests itself in the form of a crack which propagates. If the crack in a critical location goes unnoticed it could lead to a catastrophic failure of the airframe. A critical condition will occur when the stress intensity factor (SIF) at the crack tip becomes equal to fracture toughness of the material. SIF calculations will be carried out for a crack with incremental crack lengths using MVCCI method. Analytical evaluation of the crack arrest capability of the stiffening members ahead of the crack tip will be carried out. Index Terms: Key Aircraft, Design, wing, landing gear cutout, stress analysis, FEM, damage tolerance, integral stiffened panel.
Damage tolerance evaluation of wing in presence of large landing gear cutout ...eSAT Publishing House
IJRET : International Journal of Research in Engineering and Technology is an international peer reviewed, online journal published by eSAT Publishing House for the enhancement of research in various disciplines of Engineering and Technology. The aim and scope of the journal is to provide an academic medium and an important reference for the advancement and dissemination of research results that support high-level learning, teaching and research in the fields of Engineering and Technology. We bring together Scientists, Academician, Field Engineers, Scholars and Students of related fields of Engineering and Technology
International Journal of Engineering Research and Applications (IJERA) is a team of researchers not publication services or private publications running the journals for monetary benefits, we are association of scientists and academia who focus only on supporting authors who want to publish their work. The articles published in our journal can be accessed online, all the articles will be archived for real time access.
Our journal system primarily aims to bring out the research talent and the works done by sciaentists, academia, engineers, practitioners, scholars, post graduate students of engineering and science. This journal aims to cover the scientific research in a broader sense and not publishing a niche area of research facilitating researchers from various verticals to publish their papers. It is also aimed to provide a platform for the researchers to publish in a shorter of time, enabling them to continue further All articles published are freely available to scientific researchers in the Government agencies,educators and the general public. We are taking serious efforts to promote our journal across the globe in various ways, we are sure that our journal will act as a scientific platform for all researchers to publish their works online.
IJRET : International Journal of Research in Engineering and Technology is an international peer reviewed, online journal published by eSAT Publishing House for the enhancement of research in various disciplines of Engineering and Technology. The aim and scope of the journal is to provide an academic medium and an important reference for the advancement and dissemination of research results that support high-level learning, teaching and research in the fields of Engineering and Technology. We bring together Scientists, Academician, Field Engineers, Scholars and Students of related fields of Engineering and Technology.
IJRET : International Journal of Research in Engineering and Technology is an international peer reviewed, online journal published by eSAT Publishing House for the enhancement of research in various disciplines of Engineering and Technology. The aim and scope of the journal is to provide an academic medium and an important reference for the advancement and dissemination of research results that support high-level learning, teaching and research in the fields of Engineering and Technology. We bring together Scientists, Academician, Field Engineers, Scholars and Students of related fields of Engineering and Technology.
AVS 3201 Hodograph AssignmentSpring 2020Read through the L.docxjasoninnes20
AVS 3201 Hodograph Assignment
Spring 2020
Read through the Lecture AVS3201_HODOGRAPHS_AUG2019
Also Read “Hodograph Basics” in Practical Meteorology (section 14.5.1) on pages 510 through 513.
Also Read “Advanced Topic: Hodographs” in Severe and Hazardous Weather (page 30).
The basic method of plotting the hodograph is two steps:
· Plot the tip of each wind vector as a dot.
· Connect the dots.
Additionally, label each dot with a value indicating the pressure.
You will use the data handed out to you in class plot the data on your Hodograph sheet handed out in class. You only need to focus on the DRCT (wind direction) and SKNT (wind speed) columns for plotting the hodograph points. Use the PRES (pressure) column to label each point. Using knots for the wind speed is fine. Plot and label the points, then connect the dots!
Your data looks similar to this:
-----------------------------------------------------------------------------
PRES HGHT TEMP DWPT RELH MIXR DRCT SKNT THTA THTE THTV
hPa m C C % g/kg deg knot K K K
-----------------------------------------------------------------------------
980.0 178 23.8 18.8 74 14.14 190 9 298.7 340.0 301.2
965.0 312 22.6 16.6 69 12.46 196 13 298.8 335.3 301.0
932.2 610 19.8 15.1 74 11.73 210 21 298.9 333.4 301.0
925.0 677 19.2 14.8 76 11.57 210 23 298.9 332.9 301.0
899.8 914 17.3 13.7 79 11.05 215 30 299.4 331.9 301.4
898.0 931 17.2 13.6 79 11.01 216 31 299.4 331.9 301.4
868.2 1219 15.5 11.0 75 9.59 230 41 300.5 329.0 302.3
850.0 1399 14.4 9.4 72 8.78 235 42 301.2 327.4 302.8
Etc.
But don’t plot all the data! Plot the levels that are the closest to these pressure levels:
1000.0 mb
925.0 mb
875.0 mb
850.0 mb
825.0 mb
800.0 mb
750.0 mb
700.0 mb
650.0 mb
600.0 mb
550.0 mb
500.0 mb
400.0 mb
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AVS 3201 Hodograph AssignmentSpring 2020Read through the L.docxcelenarouzie
AVS 3201 Hodograph Assignment
Spring 2020
Read through the Lecture AVS3201_HODOGRAPHS_AUG2019
Also Read “Hodograph Basics” in Practical Meteorology (section 14.5.1) on pages 510 through 513.
Also Read “Advanced Topic: Hodographs” in Severe and Hazardous Weather (page 30).
The basic method of plotting the hodograph is two steps:
· Plot the tip of each wind vector as a dot.
· Connect the dots.
Additionally, label each dot with a value indicating the pressure.
You will use the data handed out to you in class plot the data on your Hodograph sheet handed out in class. You only need to focus on the DRCT (wind direction) and SKNT (wind speed) columns for plotting the hodograph points. Use the PRES (pressure) column to label each point. Using knots for the wind speed is fine. Plot and label the points, then connect the dots!
Your data looks similar to this:
-----------------------------------------------------------------------------
PRES HGHT TEMP DWPT RELH MIXR DRCT SKNT THTA THTE THTV
hPa m C C % g/kg deg knot K K K
-----------------------------------------------------------------------------
980.0 178 23.8 18.8 74 14.14 190 9 298.7 340.0 301.2
965.0 312 22.6 16.6 69 12.46 196 13 298.8 335.3 301.0
932.2 610 19.8 15.1 74 11.73 210 21 298.9 333.4 301.0
925.0 677 19.2 14.8 76 11.57 210 23 298.9 332.9 301.0
899.8 914 17.3 13.7 79 11.05 215 30 299.4 331.9 301.4
898.0 931 17.2 13.6 79 11.01 216 31 299.4 331.9 301.4
868.2 1219 15.5 11.0 75 9.59 230 41 300.5 329.0 302.3
850.0 1399 14.4 9.4 72 8.78 235 42 301.2 327.4 302.8
Etc.
But don’t plot all the data! Plot the levels that are the closest to these pressure levels:
1000.0 mb
925.0 mb
875.0 mb
850.0 mb
825.0 mb
800.0 mb
750.0 mb
700.0 mb
650.0 mb
600.0 mb
550.0 mb
500.0 mb
400.0 mb
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Evaluation of Safe Bearing Capacity by Using Statical Analysisijtsrd
This paper presents the evaluation of safe bearing capacity by using statistical analysis. Bearing capacity formulae are proposed by various researchers for various conditions. In this study, four researchers namely, Terzaghi, Meyerhof, Hansen and Vesic are selected to use the bearing capacity equations. The required soil data are taken from thirteen soil reports in Chan Aye Thar San Township which includes thirty numbers of boreholes. The bearing capacity of the soil is calculated at the depth of 6ft below ground level and the square footing is considered in this study. The safety factor of 3 is used to obtain the allowable bearing capacity for various equations. To get confidence interval by statistical analysis, the allowable bearing capacity values are divided into three portions. These are the bearing capacity values less than 2 ksf, the bearing capacity values between 2 ksf and 3 ksf, and the bearing capacity values greater than 3 ksf. Confidence interval is taken as 98 . The summary of safe bearing capacity values for different locations is described. Nyein Nyein Thant | Soe Soe War "Evaluation of Safe Bearing Capacity by Using Statical Analysis" Published in International Journal of Trend in Scientific Research and Development (ijtsrd), ISSN: 2456-6470, Volume-3 | Issue-5 , August 2019, URL: https://www.ijtsrd.com/papers/ijtsrd26565.pdfPaper URL: https://www.ijtsrd.com/engineering/civil-engineering/26565/evaluation-of-safe-bearing-capacity-by-using-statical-analysis/nyein-nyein-thant
Fluid Structural Modal Coupled Numerical Investigation of Transonic Flutterin...IJERA Editor
Flutter is an unstable oscillation which can lead to destruction. Flutter can occur on fixed surfaces, such as blades, wing or the stabilizer. By self-excited aeroelastic instability, flutter can lead to mechanical or structural failure of aircraft engine blades. The modern engines have been designed with increased pressure ratio and reduced weight in order to improve aerodynamic efficiency, resulting in severe aeroelastic problems. Particularly flutter in axial compressors with transonic flow can be characterized by a number of aerodynamic nonlinear effects such as shock boundary layer interaction, rotating stall, and tip vortex instability. Rotating blades operating under high centrifugal forces may also encounter structural nonlinearities due to friction damping and large deformations. In the future work a standard axial flow compressor blade will be taken for analysis, both Subsonic and Transonic range are taken for analysis. Fluid and Structure are two different domains which will be coupled by full system coupling technique to predict the fluttering effect on the compressor blade. ANSYS is a commercial simulation tool, which will be deployed in this work to perform FSI (Fluid Structure Interaction) and FSI coupled Modal to predict the flutter in the compressor blades
Fluid Structural Modal Coupled Numerical Investigation of Transonic Flutterin...IJERA Editor
Flutter is an unstable oscillation which can lead to destruction. Flutter can occur on fixed surfaces, such as blades, wing or the stabilizer. By self-excited aeroelastic instability, flutter can lead to mechanical or structural failure of aircraft engine blades. The modern engines have been designed with increased pressure ratio and reduced weight in order to improve aerodynamic efficiency, resulting in severe aeroelastic problems. Particularly flutter in axial compressors with transonic flow can be characterized by a number of aerodynamic nonlinear effects such as shock boundary layer interaction, rotating stall, and tip vortex instability. Rotating blades operating under high centrifugal forces may also encounter structural nonlinearities due to friction damping and large deformations. In the future work a standard axial flow compressor blade will be taken for analysis, both Subsonic and Transonic range are taken for analysis. Fluid and Structure are two different domains which will be coupled by full system coupling technique to predict the fluttering effect on the compressor blade. ANSYS is a commercial simulation tool, which will be deployed in this work to perform FSI (Fluid Structure Interaction) and FSI coupled Modal to predict the flutter in the compressor blades
Analysis of the Effect of Electric and Magnetic Loadings on the Design Parame...IJERA Editor
This paper looks at the effect of magnetic loading and electric loading on the design parameters of an induction motor and its performance. The study involves the use of MATLAB to simulate 50kW, 3-phase, 415V, 50Hz, 6 poles induction machine. Based on the variation of the magnetic and electric loading of the machine, the various design values of the rotor and stator of the machine are specified. The performance index which includes stator loss, rotor loss, cost, power factor, efficiency, and torque are also specified for squirrel cage induction motor (SCIM)
IJRET : International Journal of Research in Engineering and Technology is an international peer reviewed, online journal published by eSAT Publishing House for the enhancement of research in various disciplines of Engineering and Technology. The aim and scope of the journal is to provide an academic medium and an important reference for the advancement and dissemination of research results that support high-level learning, teaching and research in the fields of Engineering and Technology. We bring together Scientists, Academician, Field Engineers, Scholars and Students of related fields of Engineering and Technology.
AVS 3201 Hodograph AssignmentSpring 2020Read through the L.docxjasoninnes20
AVS 3201 Hodograph Assignment
Spring 2020
Read through the Lecture AVS3201_HODOGRAPHS_AUG2019
Also Read “Hodograph Basics” in Practical Meteorology (section 14.5.1) on pages 510 through 513.
Also Read “Advanced Topic: Hodographs” in Severe and Hazardous Weather (page 30).
The basic method of plotting the hodograph is two steps:
· Plot the tip of each wind vector as a dot.
· Connect the dots.
Additionally, label each dot with a value indicating the pressure.
You will use the data handed out to you in class plot the data on your Hodograph sheet handed out in class. You only need to focus on the DRCT (wind direction) and SKNT (wind speed) columns for plotting the hodograph points. Use the PRES (pressure) column to label each point. Using knots for the wind speed is fine. Plot and label the points, then connect the dots!
Your data looks similar to this:
-----------------------------------------------------------------------------
PRES HGHT TEMP DWPT RELH MIXR DRCT SKNT THTA THTE THTV
hPa m C C % g/kg deg knot K K K
-----------------------------------------------------------------------------
980.0 178 23.8 18.8 74 14.14 190 9 298.7 340.0 301.2
965.0 312 22.6 16.6 69 12.46 196 13 298.8 335.3 301.0
932.2 610 19.8 15.1 74 11.73 210 21 298.9 333.4 301.0
925.0 677 19.2 14.8 76 11.57 210 23 298.9 332.9 301.0
899.8 914 17.3 13.7 79 11.05 215 30 299.4 331.9 301.4
898.0 931 17.2 13.6 79 11.01 216 31 299.4 331.9 301.4
868.2 1219 15.5 11.0 75 9.59 230 41 300.5 329.0 302.3
850.0 1399 14.4 9.4 72 8.78 235 42 301.2 327.4 302.8
Etc.
But don’t plot all the data! Plot the levels that are the closest to these pressure levels:
1000.0 mb
925.0 mb
875.0 mb
850.0 mb
825.0 mb
800.0 mb
750.0 mb
700.0 mb
650.0 mb
600.0 mb
550.0 mb
500.0 mb
400.0 mb
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AVS 3201 Hodograph AssignmentSpring 2020Read through the L.docxcelenarouzie
AVS 3201 Hodograph Assignment
Spring 2020
Read through the Lecture AVS3201_HODOGRAPHS_AUG2019
Also Read “Hodograph Basics” in Practical Meteorology (section 14.5.1) on pages 510 through 513.
Also Read “Advanced Topic: Hodographs” in Severe and Hazardous Weather (page 30).
The basic method of plotting the hodograph is two steps:
· Plot the tip of each wind vector as a dot.
· Connect the dots.
Additionally, label each dot with a value indicating the pressure.
You will use the data handed out to you in class plot the data on your Hodograph sheet handed out in class. You only need to focus on the DRCT (wind direction) and SKNT (wind speed) columns for plotting the hodograph points. Use the PRES (pressure) column to label each point. Using knots for the wind speed is fine. Plot and label the points, then connect the dots!
Your data looks similar to this:
-----------------------------------------------------------------------------
PRES HGHT TEMP DWPT RELH MIXR DRCT SKNT THTA THTE THTV
hPa m C C % g/kg deg knot K K K
-----------------------------------------------------------------------------
980.0 178 23.8 18.8 74 14.14 190 9 298.7 340.0 301.2
965.0 312 22.6 16.6 69 12.46 196 13 298.8 335.3 301.0
932.2 610 19.8 15.1 74 11.73 210 21 298.9 333.4 301.0
925.0 677 19.2 14.8 76 11.57 210 23 298.9 332.9 301.0
899.8 914 17.3 13.7 79 11.05 215 30 299.4 331.9 301.4
898.0 931 17.2 13.6 79 11.01 216 31 299.4 331.9 301.4
868.2 1219 15.5 11.0 75 9.59 230 41 300.5 329.0 302.3
850.0 1399 14.4 9.4 72 8.78 235 42 301.2 327.4 302.8
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But don’t plot all the data! Plot the levels that are the closest to these pressure levels:
1000.0 mb
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Evaluation of Safe Bearing Capacity by Using Statical Analysisijtsrd
This paper presents the evaluation of safe bearing capacity by using statistical analysis. Bearing capacity formulae are proposed by various researchers for various conditions. In this study, four researchers namely, Terzaghi, Meyerhof, Hansen and Vesic are selected to use the bearing capacity equations. The required soil data are taken from thirteen soil reports in Chan Aye Thar San Township which includes thirty numbers of boreholes. The bearing capacity of the soil is calculated at the depth of 6ft below ground level and the square footing is considered in this study. The safety factor of 3 is used to obtain the allowable bearing capacity for various equations. To get confidence interval by statistical analysis, the allowable bearing capacity values are divided into three portions. These are the bearing capacity values less than 2 ksf, the bearing capacity values between 2 ksf and 3 ksf, and the bearing capacity values greater than 3 ksf. Confidence interval is taken as 98 . The summary of safe bearing capacity values for different locations is described. Nyein Nyein Thant | Soe Soe War "Evaluation of Safe Bearing Capacity by Using Statical Analysis" Published in International Journal of Trend in Scientific Research and Development (ijtsrd), ISSN: 2456-6470, Volume-3 | Issue-5 , August 2019, URL: https://www.ijtsrd.com/papers/ijtsrd26565.pdfPaper URL: https://www.ijtsrd.com/engineering/civil-engineering/26565/evaluation-of-safe-bearing-capacity-by-using-statical-analysis/nyein-nyein-thant
Fluid Structural Modal Coupled Numerical Investigation of Transonic Flutterin...IJERA Editor
Flutter is an unstable oscillation which can lead to destruction. Flutter can occur on fixed surfaces, such as blades, wing or the stabilizer. By self-excited aeroelastic instability, flutter can lead to mechanical or structural failure of aircraft engine blades. The modern engines have been designed with increased pressure ratio and reduced weight in order to improve aerodynamic efficiency, resulting in severe aeroelastic problems. Particularly flutter in axial compressors with transonic flow can be characterized by a number of aerodynamic nonlinear effects such as shock boundary layer interaction, rotating stall, and tip vortex instability. Rotating blades operating under high centrifugal forces may also encounter structural nonlinearities due to friction damping and large deformations. In the future work a standard axial flow compressor blade will be taken for analysis, both Subsonic and Transonic range are taken for analysis. Fluid and Structure are two different domains which will be coupled by full system coupling technique to predict the fluttering effect on the compressor blade. ANSYS is a commercial simulation tool, which will be deployed in this work to perform FSI (Fluid Structure Interaction) and FSI coupled Modal to predict the flutter in the compressor blades
Fluid Structural Modal Coupled Numerical Investigation of Transonic Flutterin...IJERA Editor
Flutter is an unstable oscillation which can lead to destruction. Flutter can occur on fixed surfaces, such as blades, wing or the stabilizer. By self-excited aeroelastic instability, flutter can lead to mechanical or structural failure of aircraft engine blades. The modern engines have been designed with increased pressure ratio and reduced weight in order to improve aerodynamic efficiency, resulting in severe aeroelastic problems. Particularly flutter in axial compressors with transonic flow can be characterized by a number of aerodynamic nonlinear effects such as shock boundary layer interaction, rotating stall, and tip vortex instability. Rotating blades operating under high centrifugal forces may also encounter structural nonlinearities due to friction damping and large deformations. In the future work a standard axial flow compressor blade will be taken for analysis, both Subsonic and Transonic range are taken for analysis. Fluid and Structure are two different domains which will be coupled by full system coupling technique to predict the fluttering effect on the compressor blade. ANSYS is a commercial simulation tool, which will be deployed in this work to perform FSI (Fluid Structure Interaction) and FSI coupled Modal to predict the flutter in the compressor blades
Analysis of the Effect of Electric and Magnetic Loadings on the Design Parame...IJERA Editor
This paper looks at the effect of magnetic loading and electric loading on the design parameters of an induction motor and its performance. The study involves the use of MATLAB to simulate 50kW, 3-phase, 415V, 50Hz, 6 poles induction machine. Based on the variation of the magnetic and electric loading of the machine, the various design values of the rotor and stator of the machine are specified. The performance index which includes stator loss, rotor loss, cost, power factor, efficiency, and torque are also specified for squirrel cage induction motor (SCIM)
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Ideal for homeowners, tech enthusiasts, and industry professionals, this presentation provides valuable insights into the trends, benefits, and future developments in smart garage technology. Stay ahead of the curve with our expert analysis and practical tips on implementing smart garage solutions.
Hello everyone! I am thrilled to present my latest portfolio on LinkedIn, marking the culmination of my architectural journey thus far. Over the span of five years, I've been fortunate to acquire a wealth of knowledge under the guidance of esteemed professors and industry mentors. From rigorous academic pursuits to practical engagements, each experience has contributed to my growth and refinement as an architecture student. This portfolio not only showcases my projects but also underscores my attention to detail and to innovative architecture as a profession.
Expert Accessory Dwelling Unit (ADU) Drafting ServicesResDraft
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Can AI do good? at 'offtheCanvas' India HCI preludeAlan Dix
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https://www.alandix.com/academic/talks/offtheCanvas-IndiaHCI2024/
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