3-D Simulation of external cooling of aero-optical side window

Under hypersonic flow environment, the aero-optical side window of optical guidance missile will trigger aero-thermodynamic effects causing high heat and cracks to optical windows which eventually leads to failure of optical windows. This study uses computational fluid dynamic as a tool to simulate hypersonic flow, optical side window cooling and jet flow design. Simulation results show that cooling effect with surface temperature less than 500K can be achieved when the external cooling jet flow reaches 0.125kg/s, thus meeting the needs of weight-bearing projectile. Since the optical side windows are located at leeward, greater angle of attack (AOA = 30) will result in a better cooling effect of the flow field under the condition with the present of AOA. Besides, the groove temperature for optical side window is similar to the temperature of cooling jet.