Theoretical characteristics in supersonic flow of constant-chord partial-span control surfaces on rectangular wings having finite thickness

Warren A. Tucker, Robert L. Nelson
naca-tn-1708
Sep 1948


The Busemann third-order approximation for two-dimensional isentropic flow was used in suitable conjunction with three-dimensional solutions found by the linearized theory to determine analytically, for small angles of attack and control deflections, the control-surface characteristics of partial-span constant-chord flaps on rectangular wings having finite thickness.

An Adobe Acrobat (PDF) file of the entire report:
http://naca.central.cranfield.ac.uk/reports/1948/naca-tn-1708.pdf