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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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