The direct simulation Monte Carlo method is used to study a plane-parallel supersonic gas flow through a grid formed by a series of parallel infinite cylinders. Characteristic features of the shock disturbance formation during the interaction of a supersonic flow with a permeable grid and the effect of this disturbance on the flow parameters behind the grid are revealed. The boundaries of the domain of supersonic flow breakup ahead of the grid and the laws of the total momentum loss on the grid are obtained. Kinetic and energetic characteristics of the flow behind the grid are determined.The interaction of rarefied gas flows with a permeable obstacle (grid) occurs in situations including the flow around wire antennas (high-altitude aerodynamics) [1], gas-dynamic deposition of films [2, 3], and gas-dynamic separation of gas mixtures [4]. It is of interest to study specific features of such flows in order to analyze acoustic disturbances generated during the interaction of jets with porous obstacles [5] and gas flows in channels of various configurations, including those with obstacles [6]. The present activities are aimed at studying transformations of the flow through an obstacle and at searching for methods of optimization of film deposition from a high-velocity rarefied gas flow passing through a grid of heated cylinders, which serves as an activator. In this case, the character of the gas flow is determined by the thermal and force actions of the cylinders on the flow. The following flow regimes can be formed:(1) supersonic flow ahead of the obstacle and behind it;(2) supersonic flow ahead of the obstacle and subsonic flow behind the obstacle;(3) nonstationary supersonic flow ahead of the obstacle and stationary subsonic or supersonic flow behind the obstacle;(4) subsonic flow ahead of the obstacle and behind it; (5) subsonic flow ahead of the obstacle and supersonic or subsonic flow behind the obstacle. In this work, we consider only situations with a plane-parallel supersonic flow ahead of the obstacle corresponding to regimes 1-3. The problem is solved by the direct simulation Monte Carlo (DSMC) method [7]. Flow transformations on the obstacle and critical regimes for various gases have similar features. Therefore, it is sufficient to study the flow of a monatomic gas without considering other particular cases.Bird [8] used the DSMC method to analyze a supersonic steam flow through a grid. Using the DSMC method, Plotnikov and Rebrov [9] studied a one-dimensional supersonic gas flow through an infinite permeable surface (zero-thickness obstacle). Characteristic features of the shock disturbance formation during the interaction of a plane-parallel supersonic flow with a permeable obstacle were revealed. The effect of the accommodation coefficient of momentum and energy of particles colliding with the obstacle surface on the macroparameters of the Kutateladze Institute of Thermophysics, Siberian Branch, Russian Academy of Sciences, Novosibirsk, 630090 Russia; plotnikov@itp.nsc.ru; rebrov@itp.nsc.ru.