# 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