This paper discusses two important forms of loading experienced by sounding rockets: the running loads due to distributed aerodynamics, and loads due to aerodynamically induced pressure differentials across the skin and across internal bulkheads. An empirical method, based upon experimental data, for the rapid and accurate determination of distributed aerodynamic loads on arbitrary bodies of revolution is outlined, and comparisons of typical results with wind-tunnel data are presented. In addition, the equations describing the venting of an "ra" volume system have been derived and a comparison of experimental with analytical results for a four-volume system subjected to a typical launch pressure profile are included.