L. A. G. Ribeiro, P. A. S. Matos, L. M. Vialta, D. Carinhana Jr., I. S. Rêgo

DOI Number XXX-YYY-ZZZ

Conference Number HiSST-2022-153

The present approach evaluated the feasibility of estimate the air mass flow rate that enters a
supersonic burner through correlations with the internal flowfield static pressure and temperature.
Experiments were carried out in a hypersonic shock tunnel facility, in a direct-connect operating mode.
The model used includes a Mach 2.7 convergent-divergent nozzle fully integrated to an isolator section
followed by a generic supersonic burner. Static pressure transducers were installed in the isolator
section, in order to measure the wall pressure of the isolator inflow. Eight different shock tunnel
conditions were tested in which the total enthalpy ranged from 950 to 2,150 kJ/kg, resulting in a
variation of the incoming airflow rate from 390 to 660 g/s. A semi-empirical correlation was preliminarily
proposed to estimate the air mass flow rate entering the model based on a linear regression fit with
coefficient of determination of 96% and residual differences less than 6%, showing to be a promising
path in the development of an air mass flow rate measurement system.

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In Categories: 1.Events, High-Speed Aerodynamics and Aerothermodynamics, HiSST 2022
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