Numerical simulation of flow inside an Orbiter wing section during entry through a hole from a possible on-orbit debris impact damage

摘要

Navier-Stokes simulations of flow inside an Orbiter wing section during entry through a hole from possible on-orbit debris impact damage were conducted. ^Flight conditions during entry at Mach 12 and 18 were chosen for the simulations. ^The flow inside the wing section was simulated with a 2D axisymmetric geometry, including an inlet representing the hole on the wing leading edge lower surface near body-point 5505, through which the flow enters the wing section, and an outlet representing the venting slot on the wing upper surface. ^The flow field inside the wing section is plumelike. ^The heat transfer to the wing section plate (front spar) due to the plume was computed. ^The convective heating and thermal environments on the wing section plate under peak-heating conditions during entry were estimated. ^(Author)