Résumé
The internal aerodynamics of a solid-propellant rocket motor is studied. The numerical simulations of two cold flow setups enable the computer code to be checked in purely aerodynamic terms. An experimental subscale setup is then described which allowed the construction of a database regarding the quasi-steady heat exchanges generated on an inert wall within the combustion chamber of a rocket motor. The computations show that an approximation which does not require the use of a very fine grid at the wall is sufficient to reproduce the measured flux levels. Moreover, a law of the wall is proposed which takes account of the effect of the steep temperature gradients and allows a better description of the measurements made. An evaluation of the ablation of a thermal insulation material placed in the combustion chamber of the test rocket motor is also presented.