  This work provides an overview of aerodynamic data acquired in the European
Transonic Windtunnel using an XRF-1 transport aircraft configuration both at
cruise conditions and at the edges of the flight envelope. The goals and design
of the wind tunnel test was described, highlighting the use of the cryogenic
wind tunnel's capability to isolate the effects of Mach and Reynolds numbers
and the dynamic pressure. The resulting dataset includes an aerodynamic
baseline characterization of the full span model with vertical and horizontal
tailplanes and without engine nacelles. The effects of different inflow
conditions were studied using data from continuous polars, evaluating the
changes in aeroelastic deformation which are proportional to $q/E$ and the
influence of $M$ and $Re$ on the shock position. Off-design data was analyzed
at the lowest and highest measured Mach numbers of 0.84 and 0.90, respectively.
Wing lower surface flow and underside shock motion was analyzed at negative
angles of attack using $c_p$ distribution and unsteady pressure transducer
fluctuation data, identifying significant upstream displacement of the shock
close to the leading edge. Wing upper side flow and the shock motion near
buffet onset and beyond was analyzed using unsteady pressure data from point
transducers and unsteady pressure sensitive paint (PSP) measurements. Buffet
occurs at lower angles of attack at high Mach number, and without clearly
defined lift break. Spectral contents at the acquired data points in the buffet
range suggest broadband fluctuations at Strouhal numbers between 0.2 and 0.6,
which is consistent with recent literature. The spanwise shock propagation
velocities were determined independently via analysis of unsteady PSP and
pressure transducers to be in the range between $u_s / u_{\infty} = 0.24$ and
$0.32$.
