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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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