Estimates have been made of the temperature history arising from aerodynamic heating of fuzes used in a number of artillery and mortar shells. The temperatures were calculated at the stagnation point, the side of the fuze, as well as at the surface and interior of the fuze. The effect of varying projectile trajectory, muzzle velocity, atmospheric conditions as well as fuze geometry and material were considered.

Shock-tube test times taking into account the boundary layer growth in argon are calculated for a variety of tube diameters and initial gas pressures. In addition, the processes involved in establishing flow in a supersonic shock tunnel are discussed. The results of two calculation procedures for determining the starting time in a shock tunnel are compared for a specific example. (Author).