Boundary Layer Control Applied to Tail Surfaces of Aircraft, Part 1. Wind Tunnel Report
Description:
Report describing the wind tunnel tests of a model of a horizontal tail surface equipped with low pressure high lift boundary layer control made to determine life, drag, pitched moment, hinge moment coefficients, and chordwise pressure distributions for various angles of attach, elevator deflections, and blowing quantity flow coefficients.
Date:
December 1957
Creator:
Leisher, L. L. & Gertsen, W. M.
Item Type:
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