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| author | Christian Kolset <christian.kolset@gmail.com> | 2025-08-25 15:22:36 -0600 |
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| committer | Christian Kolset <christian.kolset@gmail.com> | 2025-08-25 15:22:36 -0600 |
| commit | 14d4c259c26fc7ae50d64a2ab60b4e84ba45ea77 (patch) | |
| tree | 0edeca219d3ebdc714c77ac01b6de71497760e0d /tutorials/module_3 | |
| parent | 8c2a961a3a82c5b7f54137d8e8867e0c20e3fbae (diff) | |
Added links and files for module 4 & 5
Diffstat (limited to 'tutorials/module_3')
| -rw-r--r-- | tutorials/module_3/material_research.md | 40 |
1 files changed, 40 insertions, 0 deletions
diff --git a/tutorials/module_3/material_research.md b/tutorials/module_3/material_research.md new file mode 100644 index 0000000..97f9409 --- /dev/null +++ b/tutorials/module_3/material_research.md @@ -0,0 +1,40 @@ +# 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
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