초록
In this paper, a Python-based code was developed to predict the approximate performance of two-dimensional supersonic air inlets with a rectangular cross section based on compressible flow theory. The code efficiently evaluates the aerodynamic characteristics of the external compression region of multi-ramp supersonic inlets by computing the flow properties in each compression section using oblique and normal shock relations derived from user-defined geometric parameters, and automatically generates inlet configurations that satisfy a target total pressure recovery. Since the theoretical approach relies on inviscid assumptions, it may overestimate inlet performance under practical operating conditions. To address this limitation, Reynolds-Averaged Navier–Stokes simulations were conducted for selected optimal configurations to validate the preliminary design results and to quantify the degradation of total pressure recovery due to viscous effects. In addition, three-dimensional effects and the effectiveness of boundary-layer bleed devices were examined to further assess their influence on inlet performance.
이하은
박사과정
정채원
석사과정
