Interpolation algorithm for internal flow visualization of a supersonic air intake / by Rogerio Pimentel ... [et al.].: D68-6/067-2012-1E-PDF

Under the CA/NL MOU IA-6, DRDC Valcartier in Canada and TNO Defence, Security and Safety in the Netherlands jointly work to improve their numerical prediction capability on airbreathing powered missiles. As part of the collaboration program and to fill in the gap on the availability of experimental data in the open literature, wind-tunnel tests were carried out at the DRDC Valcartier tri-sonic wind-tunnel in order to gather internal aerodynamic performance data on a rectangular air intake model in isolation. The experimental data from the wind-tunnel test campaign aimed to improve the understanding of flow physics inside supersonic air intakes, to validate commercial CFD codes and to serve as input for the ramjet engine performance prediction code developed by DRDC Valcartier and TNO, the DRCORE model. Mass flow rate, pressure recovery and flow distortion at the combustor face, are outstanding parameters to support assessment of overall engine performance. The evaluation of those performance parameters is strongly dependent on the accuracy of total pressure measurements. In the wind-tunnel test campaign, total pressure measurements were obtained by means of a Pitot rake located in the combustor face of the ramjet, and then averaged in order to define a unique value for determining the performance parameters.

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