Pressure Distribution on the Fuselage of a Midwing Airplane Model at High Speeds
This is a 1939 NACA technical report on pressure distribution over the fuselage of a midwing airplane model tested at high speeds, prepared by the National Advisory Committee for Aeronautics for aerodynamic researchers and engineers. The three plates show a wind tunnel model photographed from front and rear and graphed pressure coefficient curves, offering designers a clear, monochrome reference for streamlined fuselage and wing-junction shapes and how airflow pressure changes along them.
