Investigation of Pressure and Friction Force Distributions on a Model Tail Wing Using Pressure Sensitive Paint and Surface Stress Sensitive Film

This paper describes measurement methodology and comparative results obtained using both the Pressure Sensitive Paint (PSP) and novel Surface Stress Sensitive Film (S3F) techniques. A wind tunnel test was performed by EADS together with ISSI to investigate PSP at low speeds in order to compare absolute PSP pressures and S3F relative pressure data on a typical high speed aircraft model. Furthermore the ability of the S3F film to sense wall shear stresses was demonstrated. Measurements were conducted in the flow range of 10-50 m/s, angles of attack of 10deg and 30deg and with two model configurations (with and without an air brake).