An experimental combustor, dubbed BKH, has been developed at DLR Lampoldshausen to investigate combustion instability phenomena. The combustor operates with cryogenic liquid oxygen and hydrogen
propellants at supercritical pressure conditions analogous
to real rocket engines. The BKH combustor has been
modelled using a specially developed version of the DLR
TAU code with real gas capabilities for supercritical
injection. The TAU code CFD results are compared with
optical data recorded during BKH experiments. The
numerical flame and liquid oxygen distributions match
experimental observations. The acoustic field inside the BKH combustor has also been calculated separately with an acoustic solver that uses a realistic acoustic property
distribution from the CFD calculations. The resonant modes are successfully predicted using the acoustic solver