In order to eliminate or minimize the numerical error by shock waves due to
grid distribution in multidimensional hypersonic flows. a new grid reconst
ruction scheme, the shock-aligned grid technique (SAGT), is proposed. The e
rror due to shock waves in a non-shock-aligned grid system magnifies in pro
portion to the Mach number and propagates on the downstream side of the flo
w field to contaminate sensitive aerodynamic coefficients or flow quantitie
s. SAGT, combined with the AUSMPW+ scheme proposed in Part I of the present
work, not only provides an accurate solution but also reduces the grid dep
endency of a numerical scheme without a substantial increase in computation
al cost. In addition, SAGT is robust and flexible enough to deal with compl
ex flow problems involving shock interaction and reflection and equilibrium
and nonequilibrium effects, Extensive numerical tests from a hypersonic bl
unt body flow to hypersonic nonequilibrium flows validate the accuracy, eff
iciency, robustness. and convergence characteristics of SAGT. (C) 2001 Else
vier Science.