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| author | Christian Kolset <christian.kolset@gmail.com> | 2025-04-10 15:57:05 -0600 |
|---|---|---|
| committer | Christian Kolset <christian.kolset@gmail.com> | 2025-04-10 15:57:05 -0600 |
| commit | 5611ea18eea5e34b12858fdfbb3273e4e0edf44b (patch) | |
| tree | 729766d91c0d0f29ca663d66de848968dffc80ef | |
| parent | f5ac0102057122ab29f09ca322e882681216cb62 (diff) | |
material_research.md to quote AI-generated problem statement for supersonic flow analysis
| -rw-r--r-- | material_research.md | 22 |
1 files changed, 12 insertions, 10 deletions
diff --git a/material_research.md b/material_research.md index d03551a..97f9409 100644 --- a/material_research.md +++ b/material_research.md @@ -8,16 +8,17 @@ ### 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: +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 @@ -36,3 +37,4 @@ https://kyleniemeyer.github.io/computational-thermo/content/intro-solving-proble 2D - CFD Simulation ### Thermosci MECH 338 +LMDT Analysis
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