�ݺ�ߣshows by User: shivamshivamchoubey

�ݺ�ߣshows by User: shivamshivamchoubey / http://www.slideshare.net/images/logo.gif �ݺ�ߣshows by User: shivamshivamchoubey / Wed, 09 Jun 2021 10:19:35 GMT �ݺ�ߣShare feed for �ݺ�ߣshows by User: shivamshivamchoubey Simulation Investigation of Separated Nozzle Flows /slideshow/simulation-investigation-of-separated-nozzle-flows/249246242 shivamnozzleassigment-210609101935
Simulate a convergent divergent nozzle and study the flow behaviour. • shock waves and compare with the experiment result.]]>
Simulate a convergent divergent nozzle and study the flow behaviour. • shock waves and compare with the experiment result.]]> Wed, 09 Jun 2021 10:19:35 GMT /slideshow/simulation-investigation-of-separated-nozzle-flows/249246242 shivamshivamchoubey@slideshare.net(shivamshivamchoubey) Simulation Investigation of Separated Nozzle Flows shivamshivamchoubey Simulate a convergent divergent nozzle and study the flow behaviour. • shock waves and compare with the experiment result. <img style="border:1px solid #C3E6D8;float:right;" alt="" src="https://cdn.slidesharecdn.com/ss_thumbnails/shivamnozzleassigment-210609101935-thumbnail.jpg?width=120&height=120&fit=bounds" /> Simulate a convergent divergent nozzle and study the flow behaviour. • shock waves and compare with the experiment result.

Simulation Investigation of Separated Nozzle Flows from shivam choubey

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0 steady state CFD simulation on basic shapes and calculate Cd value /slideshow/steady-state-cfd-simulation-on-basic-shapes-and-calculate-cd-value/248573745 shapeshivamchoubey-210526152013
Perform a steady-state CFD simulation on shapes and calculate value of 퐶푑. Shape used:  Square Shape  Triangle Shape  Vertical Plate]]>
Perform a steady-state CFD simulation on shapes and calculate value of 퐶푑. Shape used:  Square Shape  Triangle Shape  Vertical Plate]]> Wed, 26 May 2021 15:20:13 GMT /slideshow/steady-state-cfd-simulation-on-basic-shapes-and-calculate-cd-value/248573745 shivamshivamchoubey@slideshare.net(shivamshivamchoubey) steady state CFD simulation on basic shapes and calculate Cd value shivamshivamchoubey Perform a steady-state CFD simulation on shapes and calculate value of 퐶푑. Shape used:  Square Shape  Triangle Shape  Vertical Plate <img style="border:1px solid #C3E6D8;float:right;" alt="" src="https://cdn.slidesharecdn.com/ss_thumbnails/shapeshivamchoubey-210526152013-thumbnail.jpg?width=120&height=120&fit=bounds" /> Perform a steady-state CFD simulation on shapes and calculate value of 퐶푑. Shape used:  Square Shape  Triangle Shape  Vertical Plate

steady state CFD simulation on basic shapes and calculate Cd value from shivam choubey

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0 External Aerodynamics (Ahmed body) /shivamshivamchoubey/external-aerodynamics-ahmed-body shivamchoubeyahmd-210526151717
Perform CFD Simulation on Ahmed body and compare the CD value from literature • Literature Used : Assessment of hybrid RANS-LES formulations for flow simulation around the Ahmed body E. Guilmineau∗, G.B. Deng, A. Leroyer, P. Queutey, M. Visonneau, J. Wackers LHEEA, CNRS UMR 6598, Ecole Centrale de Nantes, 1 rue de la Noë, BP 92101, 44321 Nantes Cedex 3, France]]>
Perform CFD Simulation on Ahmed body and compare the CD value from literature • Literature Used : Assessment of hybrid RANS-LES formulations for flow simulation around the Ahmed body E. Guilmineau∗, G.B. Deng, A. Leroyer, P. Queutey, M. Visonneau, J. Wackers LHEEA, CNRS UMR 6598, Ecole Centrale de Nantes, 1 rue de la Noë, BP 92101, 44321 Nantes Cedex 3, France]]> Wed, 26 May 2021 15:17:16 GMT /shivamshivamchoubey/external-aerodynamics-ahmed-body shivamshivamchoubey@slideshare.net(shivamshivamchoubey) External Aerodynamics (Ahmed body) shivamshivamchoubey Perform CFD Simulation on Ahmed body and compare the CD value from literature • Literature Used : Assessment of hybrid RANS-LES formulations for flow simulation around the Ahmed body E. Guilmineau∗, G.B. Deng, A. Leroyer, P. Queutey, M. Visonneau, J. Wackers LHEEA, CNRS UMR 6598, Ecole Centrale de Nantes, 1 rue de la Noë, BP 92101, 44321 Nantes Cedex 3, France <img style="border:1px solid #C3E6D8;float:right;" alt="" src="https://cdn.slidesharecdn.com/ss_thumbnails/shivamchoubeyahmd-210526151717-thumbnail.jpg?width=120&height=120&fit=bounds" /> Perform CFD Simulation on Ahmed body and compare the CD value from literature • Literature Used : Assessment of hybrid RANS-LES formulations for flow simulation around the Ahmed body E. Guilmineau∗, G.B. Deng, A. Leroyer, P. Queutey, M. Visonneau, J. Wackers LHEEA, CNRS UMR 6598, Ecole Centrale de Nantes, 1 rue de la Noë, BP 92101, 44321 Nantes Cedex 3, France

External Aerodynamics (Ahmed body) from shivam choubey

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0 Airfoil Analysis(NACA 0012 ) Ansys Fluent /slideshow/airfoil-analysisnaca-0012-ansys-fluent/248573562 airfoilshivamchoubey-210526151435
Objective • This project validated and analyse NACA0012 airfoil. We are using ANSYS Fluent. • Calculate drag and lift coefficient at the airfoil Airfoil file copy and save as .txt #Group #Point #X #Y #Z 1 1 1 0 0 1 2 0.998459 0.000224 0 1 3 0.993844 0.000891 0 1 4 0.986185 0.00199 0 1 5 0.975528 0.003501 0 1 6 0.96194 0.005399 0 1 7 0.945503 0.007651 0 1 8 0.92632 0.010221 0 1 9 0.904508 0.013071 0 1 10 0.880203 0.016158 0 1 11 0.853553 0.019438 0 1 12 0.824724 0.022869 0 1 13 0.793893 0.026405 0 1 14 0.761249 0.03 0 1 15 0.726995 0.03361 0 1 16 0.691342 0.037188 0 1 17 0.654508 0.040686 0 1 18 0.616723 0.044055 0 1 19 0.578217 0.047242 0 1 20 0.53923 0.050196 0 1 21 0.5 0.052862 0 1 22 0.46077 0.055184 0 1 23 0.421783 0.057108 0 1 24 0.383277 0.058582 0 1 25 0.345492 0.059557 0 1 26 0.308658 0.059988 0 1 27 0.273005 0.059841 0 1 28 0.238751 0.059088 0 1 29 0.206107 0.057712 0 1 30 0.175276 0.055708 0 1 31 0.146447 0.053083 0 1 32 0.119797 0.049854 0 1 33 0.095492 0.046049 0 1 34 0.07368 0.041705 0 1 35 0.054497 0.036867 0 1 36 0.03806 0.03158 0 1 37 0.024472 0.025893 0 1 38 0.013815 0.019854 0 1 39 0.006156 0.013503 0 1 40 0.001541 0.006877 0 1 41 0 0 0 1 42 0.001541 -0.006877 0 1 43 0.006156 -0.013503 0 1 44 0.013815 -0.019854 0 1 45 0.024472 -0.025893 0 1 46 0.03806 -0.03158 0 1 47 0.054497 -0.036867 0 1 48 0.07368 -0.041705 0 1 49 0.095492 -0.046049 0 1 50 0.119797 -0.049854 0 1 51 0.146447 -0.053083 0 1 52 0.175276 -0.055708 0 1 53 0.206107 -0.057712 0 1 54 0.238751 -0.059088 0 1 55 0.273005 -0.059841 0 1 56 0.308658 -0.059988 0 1 57 0.345492 -0.059557 0 1 58 0.383277 -0.058582 0 1 59 0.421783 -0.057108 0 1 60 0.46077 -0.055184 0 1 61 0.5 -0.052862 0 1 62 0.53923 -0.050196 0 1 63 0.578217 -0.047242 0 1 64 0.616723 -0.044055 0 1 65 0.654508 -0.040686 0 1 66 0.691342 -0.037188 0 1 67 0.726995 -0.03361 0 1 68 0.761249 -0.03 0 1 69 0.793893 -0.026405 0 1 70 0.824724 -0.022869 0 1 71 0.853553 -0.019438 0 1 72 0.880203 -0.016158 0 1 73 0.904508 -0.013071 0 1 74 0.92632 -0.010221 0 1 75 0.945503 -0.007651 0 1 76 0.96194 -0.005399 0 1 77 0.975528 -0.003501 0 1 78 0.986185 -0.00199 0 1 79 0.993844 -0.000891 0 1 80 0.998459 -0.000224 0 1 0 ]]>
Objective • This project validated and analyse NACA0012 airfoil. We are using ANSYS Fluent. • Calculate drag and lift coefficient at the airfoil Airfoil file copy and save as .txt #Group #Point #X #Y #Z 1 1 1 0 0 1 2 0.998459 0.000224 0 1 3 0.993844 0.000891 0 1 4 0.986185 0.00199 0 1 5 0.975528 0.003501 0 1 6 0.96194 0.005399 0 1 7 0.945503 0.007651 0 1 8 0.92632 0.010221 0 1 9 0.904508 0.013071 0 1 10 0.880203 0.016158 0 1 11 0.853553 0.019438 0 1 12 0.824724 0.022869 0 1 13 0.793893 0.026405 0 1 14 0.761249 0.03 0 1 15 0.726995 0.03361 0 1 16 0.691342 0.037188 0 1 17 0.654508 0.040686 0 1 18 0.616723 0.044055 0 1 19 0.578217 0.047242 0 1 20 0.53923 0.050196 0 1 21 0.5 0.052862 0 1 22 0.46077 0.055184 0 1 23 0.421783 0.057108 0 1 24 0.383277 0.058582 0 1 25 0.345492 0.059557 0 1 26 0.308658 0.059988 0 1 27 0.273005 0.059841 0 1 28 0.238751 0.059088 0 1 29 0.206107 0.057712 0 1 30 0.175276 0.055708 0 1 31 0.146447 0.053083 0 1 32 0.119797 0.049854 0 1 33 0.095492 0.046049 0 1 34 0.07368 0.041705 0 1 35 0.054497 0.036867 0 1 36 0.03806 0.03158 0 1 37 0.024472 0.025893 0 1 38 0.013815 0.019854 0 1 39 0.006156 0.013503 0 1 40 0.001541 0.006877 0 1 41 0 0 0 1 42 0.001541 -0.006877 0 1 43 0.006156 -0.013503 0 1 44 0.013815 -0.019854 0 1 45 0.024472 -0.025893 0 1 46 0.03806 -0.03158 0 1 47 0.054497 -0.036867 0 1 48 0.07368 -0.041705 0 1 49 0.095492 -0.046049 0 1 50 0.119797 -0.049854 0 1 51 0.146447 -0.053083 0 1 52 0.175276 -0.055708 0 1 53 0.206107 -0.057712 0 1 54 0.238751 -0.059088 0 1 55 0.273005 -0.059841 0 1 56 0.308658 -0.059988 0 1 57 0.345492 -0.059557 0 1 58 0.383277 -0.058582 0 1 59 0.421783 -0.057108 0 1 60 0.46077 -0.055184 0 1 61 0.5 -0.052862 0 1 62 0.53923 -0.050196 0 1 63 0.578217 -0.047242 0 1 64 0.616723 -0.044055 0 1 65 0.654508 -0.040686 0 1 66 0.691342 -0.037188 0 1 67 0.726995 -0.03361 0 1 68 0.761249 -0.03 0 1 69 0.793893 -0.026405 0 1 70 0.824724 -0.022869 0 1 71 0.853553 -0.019438 0 1 72 0.880203 -0.016158 0 1 73 0.904508 -0.013071 0 1 74 0.92632 -0.010221 0 1 75 0.945503 -0.007651 0 1 76 0.96194 -0.005399 0 1 77 0.975528 -0.003501 0 1 78 0.986185 -0.00199 0 1 79 0.993844 -0.000891 0 1 80 0.998459 -0.000224 0 1 0 ]]> Wed, 26 May 2021 15:14:34 GMT /slideshow/airfoil-analysisnaca-0012-ansys-fluent/248573562 shivamshivamchoubey@slideshare.net(shivamshivamchoubey) Airfoil Analysis(NACA 0012 ) Ansys Fluent shivamshivamchoubey Objective • This project validated and analyse NACA0012 airfoil. We are using ANSYS Fluent. • Calculate drag and lift coefficient at the airfoil Airfoil file copy and save as .txt #Group #Point #X #Y #Z 1 1 1 0 0 1 2 0.998459 0.000224 0 1 3 0.993844 0.000891 0 1 4 0.986185 0.00199 0 1 5 0.975528 0.003501 0 1 6 0.96194 0.005399 0 1 7 0.945503 0.007651 0 1 8 0.92632 0.010221 0 1 9 0.904508 0.013071 0 1 10 0.880203 0.016158 0 1 11 0.853553 0.019438 0 1 12 0.824724 0.022869 0 1 13 0.793893 0.026405 0 1 14 0.761249 0.03 0 1 15 0.726995 0.03361 0 1 16 0.691342 0.037188 0 1 17 0.654508 0.040686 0 1 18 0.616723 0.044055 0 1 19 0.578217 0.047242 0 1 20 0.53923 0.050196 0 1 21 0.5 0.052862 0 1 22 0.46077 0.055184 0 1 23 0.421783 0.057108 0 1 24 0.383277 0.058582 0 1 25 0.345492 0.059557 0 1 26 0.308658 0.059988 0 1 27 0.273005 0.059841 0 1 28 0.238751 0.059088 0 1 29 0.206107 0.057712 0 1 30 0.175276 0.055708 0 1 31 0.146447 0.053083 0 1 32 0.119797 0.049854 0 1 33 0.095492 0.046049 0 1 34 0.07368 0.041705 0 1 35 0.054497 0.036867 0 1 36 0.03806 0.03158 0 1 37 0.024472 0.025893 0 1 38 0.013815 0.019854 0 1 39 0.006156 0.013503 0 1 40 0.001541 0.006877 0 1 41 0 0 0 1 42 0.001541 -0.006877 0 1 43 0.006156 -0.013503 0 1 44 0.013815 -0.019854 0 1 45 0.024472 -0.025893 0 1 46 0.03806 -0.03158 0 1 47 0.054497 -0.036867 0 1 48 0.07368 -0.041705 0 1 49 0.095492 -0.046049 0 1 50 0.119797 -0.049854 0 1 51 0.146447 -0.053083 0 1 52 0.175276 -0.055708 0 1 53 0.206107 -0.057712 0 1 54 0.238751 -0.059088 0 1 55 0.273005 -0.059841 0 1 56 0.308658 -0.059988 0 1 57 0.345492 -0.059557 0 1 58 0.383277 -0.058582 0 1 59 0.421783 -0.057108 0 1 60 0.46077 -0.055184 0 1 61 0.5 -0.052862 0 1 62 0.53923 -0.050196 0 1 63 0.578217 -0.047242 0 1 64 0.616723 -0.044055 0 1 65 0.654508 -0.040686 0 1 66 0.691342 -0.037188 0 1 67 0.726995 -0.03361 0 1 68 0.761249 -0.03 0 1 69 0.793893 -0.026405 0 1 70 0.824724 -0.022869 0 1 71 0.853553 -0.019438 0 1 72 0.880203 -0.016158 0 1 73 0.904508 -0.013071 0 1 74 0.92632 -0.010221 0 1 75 0.945503 -0.007651 0 1 76 0.96194 -0.005399 0 1 77 0.975528 -0.003501 0 1 78 0.986185 -0.00199 0 1 79 0.993844 -0.000891 0 1 80 0.998459 -0.000224 0 1 0 <img style="border:1px solid #C3E6D8;float:right;" alt="" src="https://cdn.slidesharecdn.com/ss_thumbnails/airfoilshivamchoubey-210526151435-thumbnail.jpg?width=120&height=120&fit=bounds" /> Objective • This project validated and analyse NACA0012 airfoil. We are using ANSYS Fluent. • Calculate drag and lift coefficient at the airfoil Airfoil file copy and save as .txt #Group #Point #X #Y #Z 1 1 1 0 0 1 2 0.998459 0.000224 0 1 3 0.993844 0.000891 0 1 4 0.986185 0.00199 0 1 5 0.975528 0.003501 0 1 6 0.96194 0.005399 0 1 7 0.945503 0.007651 0 1 8 0.92632 0.010221 0 1 9 0.904508 0.013071 0 1 10 0.880203 0.016158 0 1 11 0.853553 0.019438 0 1 12 0.824724 0.022869 0 1 13 0.793893 0.026405 0 1 14 0.761249 0.03 0 1 15 0.726995 0.03361 0 1 16 0.691342 0.037188 0 1 17 0.654508 0.040686 0 1 18 0.616723 0.044055 0 1 19 0.578217 0.047242 0 1 20 0.53923 0.050196 0 1 21 0.5 0.052862 0 1 22 0.46077 0.055184 0 1 23 0.421783 0.057108 0 1 24 0.383277 0.058582 0 1 25 0.345492 0.059557 0 1 26 0.308658 0.059988 0 1 27 0.273005 0.059841 0 1 28 0.238751 0.059088 0 1 29 0.206107 0.057712 0 1 30 0.175276 0.055708 0 1 31 0.146447 0.053083 0 1 32 0.119797 0.049854 0 1 33 0.095492 0.046049 0 1 34 0.07368 0.041705 0 1 35 0.054497 0.036867 0 1 36 0.03806 0.03158 0 1 37 0.024472 0.025893 0 1 38 0.013815 0.019854 0 1 39 0.006156 0.013503 0 1 40 0.001541 0.006877 0 1 41 0 0 0 1 42 0.001541 -0.006877 0 1 43 0.006156 -0.013503 0 1 44 0.013815 -0.019854 0 1 45 0.024472 -0.025893 0 1 46 0.03806 -0.03158 0 1 47 0.054497 -0.036867 0 1 48 0.07368 -0.041705 0 1 49 0.095492 -0.046049 0 1 50 0.119797 -0.049854 0 1 51 0.146447 -0.053083 0 1 52 0.175276 -0.055708 0 1 53 0.206107 -0.057712 0 1 54 0.238751 -0.059088 0 1 55 0.273005 -0.059841 0 1 56 0.308658 -0.059988 0 1 57 0.345492 -0.059557 0 1 58 0.383277 -0.058582 0 1 59 0.421783 -0.057108 0 1 60 0.46077 -0.055184 0 1 61 0.5 -0.052862 0 1 62 0.53923 -0.050196 0 1 63 0.578217 -0.047242 0 1 64 0.616723 -0.044055 0 1 65 0.654508 -0.040686 0 1 66 0.691342 -0.037188 0 1 67 0.726995 -0.03361 0 1 68 0.761249 -0.03 0 1 69 0.793893 -0.026405 0 1 70 0.824724 -0.022869 0 1 71 0.853553 -0.019438 0 1 72 0.880203 -0.016158 0 1 73 0.904508 -0.013071 0 1 74 0.92632 -0.010221 0 1 75 0.945503 -0.007651 0 1 76 0.96194 -0.005399 0 1 77 0.975528 -0.003501 0 1 78 0.986185 -0.00199 0 1 79 0.993844 -0.000891 0 1 80 0.998459 -0.000224 0 1 0

Airfoil Analysis(NACA 0012 ) Ansys Fluent from shivam choubey

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0 Couette flow Ansys simulation /shivamshivamchoubey/couette-flow-ansys-simulation couetteflowshivam-210526151012
Couette flow is the flow of a viscous fluid between two surfaces, one of which is moving tangentially relative and another is fixed. The relative motion of the surfaces imposes a shear stress that make flow possible.]]>
Couette flow is the flow of a viscous fluid between two surfaces, one of which is moving tangentially relative and another is fixed. The relative motion of the surfaces imposes a shear stress that make flow possible.]]> Wed, 26 May 2021 15:10:12 GMT /shivamshivamchoubey/couette-flow-ansys-simulation shivamshivamchoubey@slideshare.net(shivamshivamchoubey) Couette flow Ansys simulation shivamshivamchoubey Couette flow is the flow of a viscous fluid between two surfaces, one of which is moving tangentially relative and another is fixed. The relative motion of the surfaces imposes a shear stress that make flow possible. <img style="border:1px solid #C3E6D8;float:right;" alt="" src="https://cdn.slidesharecdn.com/ss_thumbnails/couetteflowshivam-210526151012-thumbnail.jpg?width=120&height=120&fit=bounds" /> Couette flow is the flow of a viscous fluid between two surfaces, one of which is moving tangentially relative and another is fixed. The relative motion of the surfaces imposes a shear stress that make flow possible.

Couette flow Ansys simulation from shivam choubey

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0 Mixing elbow simulation Ansys /slideshow/mixing-elbow-simulation-ansys/248573356 mixingelbow-210526150710
The objective of this study is to understand the mixing elbow problem. • Calculate Velocity distribution over bend pipe. • Calculate Temperature destruction between fluids. • Calculate and understand pressure distribution over bend pipe]]>
The objective of this study is to understand the mixing elbow problem. • Calculate Velocity distribution over bend pipe. • Calculate Temperature destruction between fluids. • Calculate and understand pressure distribution over bend pipe]]> Wed, 26 May 2021 15:07:10 GMT /slideshow/mixing-elbow-simulation-ansys/248573356 shivamshivamchoubey@slideshare.net(shivamshivamchoubey) Mixing elbow simulation Ansys shivamshivamchoubey The objective of this study is to understand the mixing elbow problem. • Calculate Velocity distribution over bend pipe. • Calculate Temperature destruction between fluids. • Calculate and understand pressure distribution over bend pipe <img style="border:1px solid #C3E6D8;float:right;" alt="" src="https://cdn.slidesharecdn.com/ss_thumbnails/mixingelbow-210526150710-thumbnail.jpg?width=120&height=120&fit=bounds" /> The objective of this study is to understand the mixing elbow problem. • Calculate Velocity distribution over bend pipe. • Calculate Temperature destruction between fluids. • Calculate and understand pressure distribution over bend pipe

Mixing elbow simulation Ansys from shivam choubey

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0 Solve the set of linear equations /slideshow/solve-the-set-of-linear-equations/248573242 linearsystem-shivamchoubey-210526150250
method solved Gauss Elimination Gauss Jordan Method]]>
method solved Gauss Elimination Gauss Jordan Method]]> Wed, 26 May 2021 15:02:50 GMT /slideshow/solve-the-set-of-linear-equations/248573242 shivamshivamchoubey@slideshare.net(shivamshivamchoubey) Solve the set of linear equations shivamshivamchoubey method solved Gauss Elimination Gauss Jordan Method <img style="border:1px solid #C3E6D8;float:right;" alt="" src="https://cdn.slidesharecdn.com/ss_thumbnails/linearsystem-shivamchoubey-210526150250-thumbnail.jpg?width=120&height=120&fit=bounds" /> method solved Gauss Elimination Gauss Jordan Method

Solve the set of linear equations from shivam choubey

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0 sin cos & tan (Plot using MATLAB) /shivamshivamchoubey/sin-cos-tan-plot-using-matlab assig3-shivamchoubey-210526145900
% plot sin cos and tan d=0:1:360; r=(pi/180)*d; s1=sin(r); c1=cos(r); t1=tan(r); grid on plot(r,s1,'-') hold on xlim([0,2*pi]) ylim([-2,2]) plot(r,c1,'r-') plot(r,t1,'b--') title("Graph of Sin(x) Cos(x) & Tan(x)") xlabel("Angles") ylabel("Values") grid on grid minor legend("sin(x)","cos(x)","tan(x)")]]>
% plot sin cos and tan d=0:1:360; r=(pi/180)*d; s1=sin(r); c1=cos(r); t1=tan(r); grid on plot(r,s1,'-') hold on xlim([0,2*pi]) ylim([-2,2]) plot(r,c1,'r-') plot(r,t1,'b--') title("Graph of Sin(x) Cos(x) & Tan(x)") xlabel("Angles") ylabel("Values") grid on grid minor legend("sin(x)","cos(x)","tan(x)")]]> Wed, 26 May 2021 14:59:00 GMT /shivamshivamchoubey/sin-cos-tan-plot-using-matlab shivamshivamchoubey@slideshare.net(shivamshivamchoubey) sin cos & tan (Plot using MATLAB) shivamshivamchoubey % plot sin cos and tan d=0:1:360; r=(pi/180)*d; s1=sin(r); c1=cos(r); t1=tan(r); grid on plot(r,s1,'-') hold on xlim([0,2*pi]) ylim([-2,2]) plot(r,c1,'r-') plot(r,t1,'b--') title("Graph of Sin(x) Cos(x) & Tan(x)") xlabel("Angles") ylabel("Values") grid on grid minor legend("sin(x)","cos(x)","tan(x)") <img style="border:1px solid #C3E6D8;float:right;" alt="" src="https://cdn.slidesharecdn.com/ss_thumbnails/assig3-shivamchoubey-210526145900-thumbnail.jpg?width=120&height=120&fit=bounds" /> % plot sin cos and tan d=0:1:360; r=(pi/180)*d; s1=sin(r); c1=cos(r); t1=tan(r); grid on plot(r,s1,'-') hold on xlim([0,2*pi]) ylim([-2,2]) plot(r,c1,'r-') plot(r,t1,'b--') title("Graph of Sin(x) Cos(x) & Tan(x)") xlabel("Angles") ylabel("Values") grid on grid minor legend("sin(x)","cos(x)","tan(x)")

sin cos & tan (Plot using MATLAB) from shivam choubey

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0 The Singular Value Decomposition theroy + example /slideshow/the-singular-value-decomposition-theroy-example/248573023 svd-210526145602
SVD coding - img=imread("img.png");% Reading image B=im2double(img);% coverting to double precsion image imgBlack=rgb2gray(B); %imshow(imgBlack); [U S V]=svd(imgBlack); [U1 S1 V1]=svd(imgBlack,'econ'); ylabel("Singuler value") xlabel("value") plot(diag(S1),'o k') ]]>
SVD coding - img=imread("img.png");% Reading image B=im2double(img);% coverting to double precsion image imgBlack=rgb2gray(B); %imshow(imgBlack); [U S V]=svd(imgBlack); [U1 S1 V1]=svd(imgBlack,'econ'); ylabel("Singuler value") xlabel("value") plot(diag(S1),'o k') ]]> Wed, 26 May 2021 14:56:02 GMT /slideshow/the-singular-value-decomposition-theroy-example/248573023 shivamshivamchoubey@slideshare.net(shivamshivamchoubey) The Singular Value Decomposition theroy + example shivamshivamchoubey SVD coding - img=imread("img.png");% Reading image B=im2double(img);% coverting to double precsion image imgBlack=rgb2gray(B); %imshow(imgBlack); [U S V]=svd(imgBlack); [U1 S1 V1]=svd(imgBlack,'econ'); ylabel("Singuler value") xlabel("value") plot(diag(S1),'o k') <img style="border:1px solid #C3E6D8;float:right;" alt="" src="https://cdn.slidesharecdn.com/ss_thumbnails/svd-210526145602-thumbnail.jpg?width=120&height=120&fit=bounds" /> SVD coding - img=imread("img.png");% Reading image B=im2double(img);% coverting to double precsion image imgBlack=rgb2gray(B); %imshow(imgBlack); [U S V]=svd(imgBlack); [U1 S1 V1]=svd(imgBlack,'econ'); ylabel("Singuler value") xlabel("value") plot(diag(S1),'o k')

The Singular Value Decomposition theroy + example from shivam choubey

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0 1-D Steady Heat conduction FDM /slideshow/1d-steady-heat-conduction-fdm/248572936 1dsteadystatefdmshivamchoubey-210526145313
FDM method : Matlab code]]>
FDM method : Matlab code]]> Wed, 26 May 2021 14:53:13 GMT /slideshow/1d-steady-heat-conduction-fdm/248572936 shivamshivamchoubey@slideshare.net(shivamshivamchoubey) 1-D Steady Heat conduction FDM shivamshivamchoubey FDM method : Matlab code <img style="border:1px solid #C3E6D8;float:right;" alt="" src="https://cdn.slidesharecdn.com/ss_thumbnails/1dsteadystatefdmshivamchoubey-210526145313-thumbnail.jpg?width=120&height=120&fit=bounds" /> FDM method : Matlab code

1-D Steady Heat conduction FDM from shivam choubey

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0 The finite volume method for diffusion problems /shivamshivamchoubey/the-finite-volume-method-for-diffusion-problems fvmshivam-210526145042
Matlab code for diffusion problem. An Introduction to Computational Fluid Dynamics: The Finite Volume Method Book by H. K. Versteeg and W. Malalasekera (4.1 (page 119) ]]>
Matlab code for diffusion problem. An Introduction to Computational Fluid Dynamics: The Finite Volume Method Book by H. K. Versteeg and W. Malalasekera (4.1 (page 119) ]]> Wed, 26 May 2021 14:50:41 GMT /shivamshivamchoubey/the-finite-volume-method-for-diffusion-problems shivamshivamchoubey@slideshare.net(shivamshivamchoubey) The finite volume method for diffusion problems shivamshivamchoubey Matlab code for diffusion problem. An Introduction to Computational Fluid Dynamics: The Finite Volume Method Book by H. K. Versteeg and W. Malalasekera (4.1 (page 119) <img style="border:1px solid #C3E6D8;float:right;" alt="" src="https://cdn.slidesharecdn.com/ss_thumbnails/fvmshivam-210526145042-thumbnail.jpg?width=120&height=120&fit=bounds" /> Matlab code for diffusion problem. An Introduction to Computational Fluid Dynamics: The Finite Volume Method Book by H. K. Versteeg and W. Malalasekera (4.1 (page 119)

The finite volume method for diffusion problems from shivam choubey

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0 https://cdn.slidesharecdn.com/profile-photo-shivamshivamchoubey-48x48.jpg?cb=1739037505 www.linkedin.com/in/shivam-choubey-b935772a/ https://cdn.slidesharecdn.com/ss_thumbnails/shivamnozzleassigment-210609101935-thumbnail.jpg?width=320&height=320&fit=bounds slideshow/simulation-investigation-of-separated-nozzle-flows/249246242 Simulation Investigati... https://cdn.slidesharecdn.com/ss_thumbnails/shapeshivamchoubey-210526152013-thumbnail.jpg?width=320&height=320&fit=bounds slideshow/steady-state-cfd-simulation-on-basic-shapes-and-calculate-cd-value/248573745 steady state CFD simul... https://cdn.slidesharecdn.com/ss_thumbnails/shivamchoubeyahmd-210526151717-thumbnail.jpg?width=320&height=320&fit=bounds shivamshivamchoubey/external-aerodynamics-ahmed-body External Aerodynamics ...