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# 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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