Numerical estimations of peak heat flux at throat of liquid rocket engines

The problem of prediction of peak heat flux at throat of liquid rocket engines still constitutes a challenge, also because of the limited experimental information. Recently, a number of experimental tests have been usefully made available to scientific community, aiming to improve prediction fidelity. In this paper, a comparison of dierent approaches based on dierent levels of model completeness is carried out aiming to evaluate limits and capabilities of each of them. In particular, the role of detailed combustion modeling and boundary layer modeling is discussed in comparison with experimental data for the single and seven injector GO2/GCH4 test cases developed at Technical University of Munich.