Longitudinal stability and control characteristics of a semispan airplane model with a swept-back tail from tests at transonic speeds by the NACA wing-flow method
Description: Report presenting an investigation using the NACA wing-flow method to determine the longitudinal stability and control characteristics of a semispan airplane model with a wing of conventional plan form and a horizontal tail swept back 45 degrees at transonic speeds. Measurements were made of lift and angle of attack for trim at several stabilizer and elevator settings.
Date: March 28, 1947
Creator: Zalovcik, John A. & Sawyer, Richard H.
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