DESIGN OF A WIND TUNNEL MODEL FOR A REUSABLE LAUNCH VEHICLE DURING ITS LANDING BURN

Abstract

This paper outlines the design process for a wind tunnel model of a reusable launch vehicle (RLV) during its landing burn. The development of the model occurs in three main phases. Initially, the design is created based on assumed nozzle flow conditions, ensuring that the key parameters of the testing conditions are matched with those of the flight conditions. Subsequently, the prototype is printed and used to measure the actual nozzle flow conditions using a newly developed measurement system. Upon acquiring the actual parameters, the model is finalised, featuring a nozzle throat diameter of 5 mm, an expansion ratio of 1.115, a base diameter of 21 mm, and a length of 300 mm. This model satisfies the retropropulsion similarity criteria with an aerodynamic thrust coefficient CT = 124.4 and an ambient pressure ratio APR = 0.762. CFD simulations are used to complement experimental data and examine the flowfield around the wind tunnel model. It was observed that a supersonic jet is achieved and a large recirculation region forms along its length.