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| .p21 boundary layer thickness $ \delta ∝ {M_∞}^2 / sqrt{ R_{e_x} } $ where $ R_{e_x} $ is the local Reynolds number | .p21 boundary layer thickness $ \delta ~ \propto ~ {M_∞}^2 / \sqrt{ R_{e_x} }$ where $ R_{e_x} $ is the local Reynolds number |
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| .p29 $ p $ surface pressure, $ \tau $ shear stress | .p29 $ p $ surface pressure, $ \tau $ shear stress (viscous flow phenomena) |
Hypersonic Notes
- inviscid - laminar, low turbulence, low Reynolds number
Modern compressible flow : with historical perspective John David Anderson, Jr 1982 PSU QA911 .A6
Hypersonic and High Temperature Gas Dynamics
John David Anderson Jr 2000 AIAA page numbers in concatenated pdf
- p11 Apollo reentry Mach 36
- p19 M36 15 degree cone, 3 degree shock layer
calorically perfect gas, γ = cp/cv = 1.4 ratio of specific heats
p21 boundary layer thickness \delta ~ \propto ~ {M_∞}^2 / \sqrt{ R_{e_x} } where R_{e_x} is the local Reynolds number
- p22 Reynolds number ... per foot?
- p23 Apollo reentry Mach 36, 52 km altitude, 11000 Kelvin (40x denser than 80 km, 1200x denser than 100 km)
- p24 chemically reacting gas is colder
- p25 O₂ dissociates at 2000K to 4000K, N₂ 4000K to 9000K, above that ions
p25 convective heating q_c, radiative heating q_r 30% for Apollo
- p26 100 km, low density flow, "velocity slip" and "temperature slip" at surface
- p26 higher still, not continuum, use kinetic theory. At 150 km, free molecular regime
p27 Knudsen number, Kn = \lambda/L where \lambda = mean free path, L = characteristic length
Kn 0.001? to 0.3 Navier-Stokes
p29 p surface pressure, \tau shear stress (viscous flow phenomena)
- p795 references