<p>Impinging supersonic flow is highly intricate, influenced by diverse shock types and numerous factors. Rocket hot gas launchers, particularly concentric canister launchers, exemplify this phenomenon. This research employs computational fluid dynamics to investigate various end shapes of the canister in order to minimize its pressure. Based on the numerical solution, the hemispherical aft-end shape at the distance equal to 2 times the nozzle’s exit radius from the nozzle exit, yields the lowest pressure, and based on it, an experimental model was constructed. The head-end of the model was closed with a composite frangible cover. Using a solid propellant gas generator with a 0.7-s burning time as the working fluid, the study has examined the impact of the hot gas supersonic jet on the laboratory canister components. According to the test results, the maximum pressure does not occur at the center of the hemisphere. The high-pressure region around 3 bar before head-end cover fracture is limited to a sector of 30 degrees of the hemisphere aft end and does not exceed 1.5 bar in the other regions of the concentric canister launchers. The pressure at all points in the canister reaches ambient pressure immediately after the head cover fractures, and only the pressure at the center location begins to decrease after 0.3 s. The high accuracy of the numerical method in the simulation of the unsteady pressure behavior in the laboratory canister components could be used to confirm the hemispherical shape proposed for lower pressure at the end of the canister, and pressure prediction of the larger canisters. Data from the present experimental test, before and after the cover fracture, could be used to lighten the canister weight.</p>