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+# Assignment Material Research
+
+## Numerical Differentiation and Integration Applications
+
+
+### Vibrations
+
+
+### Supersonic
+
+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​
+Use 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