Tests of a Horizontal-Tail Model through the Transonic Speed Range by the NACA Wing-Flow Method
Description:
"A 1/12-scale model of a horizontal tail of a fighter airplane was tested through the transonic speeds in the high-speed flow over an airplane wing, the surface of which served as a reflection plane for the model. Measurements of lift, elevator-hinge moment, angle of attack, and elevator angle were made in the Mach number range from 0.75 to 1.04 for elevator deflections ranging from 10 degrees to minus 10 degrees, and for angles of attack of minus 1.2 degrees, 0.4 degrees, and 3.4 degrees. The …
more
Date:
April 11, 1947
Creator:
Adams, Richard E. & Silsby, Norman S.
Item Type:
Refine your search to only
Report
Partner:
UNT Libraries Government Documents Department