Hypersonic Notes

inviscid - laminar, low turbulence, low Reynolds number
Modern compressible flow : with historical perspective John David Anderson, Jr 1982 PSU QA911 .A6

John David Anderson Jr 2000 AIAA page numbers in book, pdf+6

p05 Apollo reentry Mach 36
p13 M36 15 degree cone, 3 degree shock layer
- calorically perfect gas, γ = c_p/c_v = 1.4 ratio of specific heats
p15 boundary layer thickness \delta ~ \propto ~ {M_∞}^2 / \sqrt{ R_{e_x} } where R_{e_x} is the local Reynolds number
p16 Reynolds number ... per foot?
p17 Apollo reentry Mach 36, 52 km altitude, 11000 Kelvin (40x denser than 80 km, 1200x denser than 100 km)
p18 chemically reacting gas is colder
p19 O₂ dissociates at 2000K to 4000K, N₂ 4000K to 9000K, above that ions
p19 convective heating q_c, radiative heating q_r 30% for Apollo
p20 100 km, low density flow, "velocity slip" and "temperature slip" at surface
p20 higher still, not continuum, use kinetic theory. At 150 km, free molecular regime
p21 Knudsen number, Kn = \lambda/L where \lambda = mean free path, L = characteristic length
- Kn 0.001? to 0.3 Navier-Stokes
p23 p surface pressure, \tau shear stress (viscous flow phenomena)
p26 heat conduction q_w ~ = -k_w \left( { { \partial T } \over { \partial y } } \right)_w ... more in Part 2
p26 radiation 30% Apollo, shock layer 11,000K ... more Chapter 18