Corneliu STOICA, Alexandru MARIN, Emanuel TRANDAFIR, Alexandru PANA, Catalin NAE, Alexandru NICA, Sorin DEFTA, Ionut BUNESCU, Gilbert STOICAN, Dumitru CURT, Johan Steelant
DOI Number XXX-YYY-ZZZ
Conference Number HiSST-2022-280
A key point for different space missions, including satellite lunching and future space tourism, is the
fuel consumption, which is linked to the propulsion system optimization. From the information related
to actual aeronautical programs for supersonic jets and from published flight measurements of space
launchers (Ariane5 and VEGA), it was concluded that currently used approach (CFD and wind tunnel
testing) underestimates the base pressure and hence overestimates the vehicle drag. This is mainly
due to the influence of the plume temperature on the complex flow field surrounding the base region,
leading also to a large uncertainty in the heat loads and fluctuating loads on the nozzle. As a result
from current investigations on the capabilities in Europe with respect to the active models simulations
for space applications, INCAS has identified a real need for a facility able to provide this very specific
capability for improved predictions. Traditionally INCAS supersonic wind tunnel, as many other wind
tunnels, used cold plumes to simulate the jet-on conditions in tests, for flight ranging from transonic to
supersonic conditions. This paper describes the work on the last development program aimed to
enhance INCAS Supersonic Wind Tunnel testing capability by introducing hot plume testing capability
under similitude conditions for space vehicles. This capability is based on a dedicated supply system for
hydrogen peroxide, used as a monopropellant for the rocket engine system simulator, to be used
complementary with the existing cold air supply system for jet simulations. Following this goal, we
introduce a generic calibration model for base drag evaluation under similitude criteria. The built wind
tunnel model is using a generic launcher configuration installed on a dedicated support, including a
peroxide engine simulator able to simulate hot plume interactions in transonic and supersonic regimes
and a secondary air flux. During testing it is possible to measure the global loads and pressure surface
measurements using specific instrumentation of the model, contributing to the development of a set of
scaling parameters and similitude factors for active rocket engines simulations in wind tunnels. The
proposed approach goal is to improve the knowledge related to interaction between rocket exhaust
plumes and the base region leading to an optimized launcher design. The basic work performed was
taking into account the need for the new supply system to be qualified with respect to safety procedures
needed for standard usage in wind tunnel tests at INCAS. Also, as a result from the test campaign, one
engine testing rig was developed, able to measure the hydrogen peroxide engines parameters before
they are installed on the wind tunnel model.