This paper discusses the wind tunnel test of a 37.5% scale model of a blended wing body unmanned aerial vehicle. The model was mounted on a fixed belly-fairing sting, and the pitch variation was facilitated via a linear actuator. The model and set-up were directly mounted on a force plate placed underneath the tunnel floor. Aerodynamic loads were acquired at a range of wind tunnel velocities between 10m/s and 30m/s, corresponding to a Reynolds number range between ∼246 000 and ∼760 000, and results show good repeatability throughout the experimental campaign. A virtual wing tunnel was set up using computational fluid dynamics representative of the real-life facility, and the model was simulated inside the tunnel for a range of angles of attack between -4deg and 10deg without support, and at a reduced range between 0deg and 6deg with the support “installed.” Classical analytical methods for boundary and support interference corrections were implemented, and corrections factors were estimated by numerical simulation of the model with and without the support installed. Preliminary comparison between experimental measurements from force balance and numerical data show satisfactory agreement in the prediction of the lift curve slope, with some disagreement in the prediction of the stall condition. Prediction of drag and pitching moment are significantly impacted by the presence of the support and show poor agreement with numerical data.