Hypersonic, viscous shock layer with chemical nonequilibrium for spherically blunted cones.
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Engineering topics
Publications and source records attributed to Kang, S.-W..
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Application of a viscous shock-layer analysis to the calculation of nonequilibrium-flow species distributions in the plasma layer of a blunt-nosed vehicle at high altitudes. The theoretical electron-density results obtained are in good agreement with those measured in flight for a hemisphere-9 deg cone entry vehicle. The flight measurements were obtained using electrostatic probes that protruded well into the shock layer. In addition, the theoretically obtained heavy-particle translational temperatures appear to agree fairly well with the electron temperatures that were measured in the flight experiments using voltage-swept thin-wire electrostatic probes. The influence of the reaction rate coefficients on the calculated electron densities has been assessed and shown to be within the uncertainty in the flight data. The theoretical results demonstrate the importance of including in the chemical model the positive ions N2(+), O2(+), N(+), and O(+), in addition to NO(+), for the high altitudes and velocities considered.
Nonequilibrium ionized hypersonic flow over blunt body at low Reynolds number, using thin shock layer assumption in analysis
Mass injection effects on viscous hypersonic low Reynolds number shock layer downstream and at stagnation point in blunt forebody region analyzed for nonreacting gas
Integral method analysis for hypersonic viscous shock layer with mass injection
Integral method analysis of blowing effects on viscous hypersonic shock layer about blunt body for stagnation region
Viscous hypersonic shock layer over blunt bodies at low Reynolds number
Mass injection effect on compressible three- dimensional laminar boundary layers analyzed for nonreacting gas, using conservation equations for flow velocity profiles