A convex shell structure for enhanced aerodynamic performance and/or
reduced heat transfer requirements for a space vehicle that re-enters an
atmosphere. The structure has a fore-body, an aft-body, a longitudinal
axis and a transverse cross sectional shape, projected on a plane
containing the longitudinal axis, that includes: first and second linear
segments, smoothly joined at a first end of each the first and second
linear segments to an end of a third linear segment by respective first
and second curvilinear segments; and a fourth linear segment, joined to a
second end of each of the first and second segments by curvilinear
segments, including first and second ellipses having unequal ellipse
parameters. The cross sectional shape is non-symmetric about the
longitudinal axis. The fourth linear segment can be replaced by a sum of
one or more polynomials, trigonometric functions or other functions
satisfying certain constraints.