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diff --git a/material_research.md b/material_research.md deleted file mode 100644 index 97f9409..0000000 --- a/material_research.md +++ /dev/null @@ -1,40 +0,0 @@ -# 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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