This report presents the results of an investigation conducted in the Langley 300 mph 7- 10-foot wind tunnel for the purpose of determining the aerodynamic characteristics of a model wing-propeller combination, and of the wing and propeller separately at angles of attack up to 90 degrees. The tests covered thrust coefficients corresponding to free-stream velocities from zero forward speed to the normal range of cruising speeds. The results indicate that increasing the thrust coefficient increases the angle of attack for maximum lift and greatly diminishes the usual reduction in lift above the angle of attack for maximum lift.

The aerodynamic characteristics of a wing-propeller combination with the propeller rotating in the wing-chord plane of a two-dimensional wing were investigated. The wing had a 4-1/2-foot chord length. Total static lift was measured with and without the wing for a 3-foot-diameter propeller; the effects of a ground plane on the static lift of the wing-propeller combination were measured with a 2-foot-diameter propeller. Lift and pressure distributions at several angles of attack and free-stream airspeeds from 0 to 93 feet per second were obtained with the 3j-foot diameter wing-propeller combination.