Direct calculation of aerodynamic force derivatives - A sensitivity-equation approach

Abstract

The objective of the present work is to investigate the sensitivity-equation approach to computing stability derivatives using a single non-linear solution to the Navier-Stokes equations. The sensitivity equations are presented in integral form with the necessary boundary conditions. Flow computations are presented for a flat plate boundary layer for validation. The lift-curve slope is computed at several angles of attack for a laminar airfoil. Stability characteristics are analyzed for the YB-49 flying wing.