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An experimental program was set up in the CERT/ONERA's T2 wind tunnel, which is transonic, pressurized, and has self-adaptive walls. A l/80th-scale model of a modern transonic transport aircraft was tested in two configurations: 1) fuselage without horizontal stabilizer and 2) fuselage with horizontal stabilizer. Various measurements were performed: oil-flow visualizations, pressure distributions, boundary-layer surveys along the fuselage symmetry lines using a three-dimensional laser Doppler anemometry system, and wake surveys with both pressure and velocity measurements in a plane downstream of the fuselage base. Moreover, both inviscid and viscous computations were carried out separately under experimental conditions. This article reports a detailed analysis of the computations and experiments conducted on the model in both configurations; the objective of this study was to reach a better understanding of the flows developing along the rear part of a fuselage.

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