An analysis of hypersonic flow over a wedge and cone is developed that
is based on hypersonic small-disturbance theory in combination with l
aminar boundary-layer theory. The parameters that determine the flow a
re the ratio of specific heats (=1.4), the freestream Mach number, whi
ch ranges from 4 to 10, the wall half-angle, equal to 5, 10, or 15 deg
, a wall to freestream temperature ratio, equal to 1 or 3, a Reynolds
number (=10(6), and a geometric parameter that is zero for a wedge and
unity for a cone. All results are nondimensional and in a convenient
form for establishing trends or for comparisons with experimental or C
FD data. Results are provided for the inviscid surface values of the p
ressure, temperature, and Mach number; wave and viscous drag coefficie
nts and several heat transfer coefficients; the maximum temperature an
d its location inside the boundary layer; and a variety of viscous and
thermal boundary-layer thicknesses. The independent parameter is the
freestream Mach number; the dependence on the wall to freestream tempe
rature ratio and a Reynolds number are explicitly given.