From 5611ea18eea5e34b12858fdfbb3273e4e0edf44b Mon Sep 17 00:00:00 2001 From: Christian Kolset Date: Thu, 10 Apr 2025 15:57:05 -0600 Subject: material_research.md to quote AI-generated problem statement for supersonic flow analysis --- material_research.md | 22 ++++++++++++---------- 1 file changed, 12 insertions(+), 10 deletions(-) (limited to 'material_research.md') 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 \ No newline at end of file -- cgit v1.2.3