Numerical Analysis on the Characteristics of the Exhaust Plume During the Re-Entry Phase of Vertical Landing Reusable Launch Vehicle Under Different Altitude

In order to examine the characteristics of the exhaust plume during the re-entry phase of vertical landing reusable launch vehicle, a supersonic high-altitude plume model is developed using two-dimensional multicomponent Navier-Stokes equations and realizable k-ε turbulence model. The flow field of the launch vehicle at altitudes of 0 km, 5 km, 10 km, 15 km, 20 km and 25 km is calculated using the discrete ordinates method and the second-order total variation diminishing (TVD) upwind scheme. The findings indicate that as altitude decreases, the length of the plume experiences an initial increase, followed by a decrease, and then increases again, while the surface temperature of the rocket gradually decreases, and the angle of the shockwave increases. The temperature on the rocket side wall decreases linearly as the distance from the nozzle increases. On the other hand, the temperature on the rocket base increases and changes parabolically as the distance from the axis decreases. This paper reveals the characteristics of the exhaust plume in the re-entry stage of the vertical landing reusable launch vehicle. The research results have theoretical and engineering significance for the design of the re-entry stage of the vertical landing reusable launch vehicle.