| # | Short Problem Description | Manual solution Inactive links |
Computer solution Inactive links |
|---|---|---|---|
| 1 |  Velocity and Mach number |
q01.pdf | q01.py |
| 2 |  Convergent-divergent duct |
q02.pdf | q02.py |
| 3 |  Exhaust gases from a rocket engine |
q03.pdf | q03.py |
| 4 |  Exhaust gases from a rocket engine |
q04.pdf | q04.py |
| 5 |  Pressure, temperature and Mach number |
q05.pdf | q05.py |
| 6 |  Carbon dioxide flow |
q06.pdf | q06.py |
| 7 | Stagnation pressure and temperature | q07.pdf | q07.py |
| 8 | Helium flow | q08.pdf | q08.py |
| 9 | Argon flow | q09.pdf | q09.py |
| 10 |  Stagnation pressure and temperature |
q10.pdf | q10.py |
| 11 | Maximum possible velocity | q11.pdf | q11.py |
| 12 |  Pitot-static tube |
q12.pdf | q12.py |
| 13 | Pitot-static tube | q13.pdf | q13.py |
| 14 | Pitot tube | q14.pdf | q14.py |
| 15 | Pitot tube | q15.pdf | q15.py |
| 16 | Pitot tube (CO2) | q16.pdf | q16.py |
| 17 |  Isentropic flow through a duct |
q17.pdf | q17.py |
| 18 |  Liquid fuelled rocket |
q18.pdf | q18.py |
| 19 |  Flow through a duct |
q19.pdf | q19.py |
| 20 |  Diffuser at the intake of the engine |
q20.pdf | q20.py |
| 21 |  Conical diffuser |
q21.pdf | q21.py |
| 22 |  Thrust control |
q22.pdf | q22.py |
| 23 |  Imperial units |
q23.pdf | q23.py |
| 24 |  Highest pressure on aircraft |
q24.pdf | q24.py |
| 25 | Stagnation pressure and temperature | q25.pdf | q25.py |
| 26 |  Speed and the Mach number |
q26.pdf | q26.py |
| 27 |  Compressible vs incompressible |
q27.pdf | q27.py |
| 28 |  Imperial units |
q28.pdf | q28.py |
| 29 |  Rocket engine |
q29.pdf | q29.py |
| 30 | Mach number and the stagnation temperature | q30.pdf | q30.py |
| 31 |  Pipe flow |
q31.pdf | q31.py |
| 32 |  Exit door window failure |
q32.pdf | q32.py |