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authorChristian Kolset <christian.kolset@gmail.com>2025-08-25 15:22:36 -0600
committerChristian Kolset <christian.kolset@gmail.com>2025-08-25 15:22:36 -0600
commit14d4c259c26fc7ae50d64a2ab60b4e84ba45ea77 (patch)
tree0edeca219d3ebdc714c77ac01b6de71497760e0d /tutorials
parent8c2a961a3a82c5b7f54137d8e8867e0c20e3fbae (diff)
Added links and files for module 4 & 5
Diffstat (limited to 'tutorials')
-rw-r--r--tutorials/module_3/material_research.md40
-rw-r--r--tutorials/module_4/data_processing.md1
-rw-r--r--tutorials/module_4/data_visualization.md1
-rw-r--r--tutorials/module_4/importing_scientific_data.md1
-rw-r--r--tutorials/module_4/plotting.md1
-rw-r--r--tutorials/module_5/neural_networks.md2
-rw-r--r--tutorials/module_5/supervised_vs_unsupervised_learning.md2
7 files changed, 48 insertions, 0 deletions
diff --git a/tutorials/module_3/material_research.md b/tutorials/module_3/material_research.md
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+# Assignment Material Research
+
+## Numerical Differentiation and Integration Applications
+
+
+### Vibrations
+
+
+### Supersonic
+
+AI Generated Problem:
+> An aircraft flying at supersonic speed (Mach > 1) can experience normal shock waves in the engine intake or around the airframe. A normal shock causes a sudden drop in Mach number and changes in flow properties.
+>
+> Assume air behaves as an ideal gas with specific heat ratio γ=1.4γ=1.4.
+>
+> You are given the upstream Mach number M1M1​, and you need to compute the following properties after the shock:
+> Downstream Mach number M2M2​
+> Ratio of pressures P2/P1P2​/P1​
+> Ratio of temperatures T2/T1T2​/T1​
+> Ratio of densities ρ2/ρ1ρ2​/ρ1​
+> Using the following equations for a normal shock:
+
+### Mechatronics - MECH 207/307
+Loads on a circuit
+
+### Statics Problems - CIVE 260
+Loads on a bridge
+
+
+### Dynamics of Machines - MECH 324
+Modelling of Fourbar linkakes
+
+### Thermo - MECH 339/439
+https://kyleniemeyer.github.io/computational-thermo/content/intro-solving-problems.html
+
+### Heat and Mass Transfer - MECH 344
+2D - CFD Simulation
+
+### Thermosci MECH 338
+LMDT Analysis \ No newline at end of file
diff --git a/tutorials/module_4/data_processing.md b/tutorials/module_4/data_processing.md
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+# Data Processing
diff --git a/tutorials/module_4/data_visualization.md b/tutorials/module_4/data_visualization.md
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+# Data Visualization
diff --git a/tutorials/module_4/importing_scientific_data.md b/tutorials/module_4/importing_scientific_data.md
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+# Importing Scientific Data \ No newline at end of file
diff --git a/tutorials/module_4/plotting.md b/tutorials/module_4/plotting.md
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+++ b/tutorials/module_4/plotting.md
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# Plotting
## matlibplot
+
diff --git a/tutorials/module_5/neural_networks.md b/tutorials/module_5/neural_networks.md
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+# Neural Networks
+
diff --git a/tutorials/module_5/supervised_vs_unsupervised_learning.md b/tutorials/module_5/supervised_vs_unsupervised_learning.md
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+# Supervised vs unsupervised learning
+