Publication Date:
2019-07-13
Description:
Force and moment measurements from an F-16XL during forced pitch oscillation tests result in dynamic stability derivatives, which are measured in combinations. Initial computational simulations of the motions and combined derivatives are attempted via a low-order, time-dependent panel method computational fluid dynamics code. The code dynamics are shown to be highly questionable for this application and the chosen configuration. However, three methods to computationally separate such combined dynamic stability derivatives are proposed. One of the separation techniques is demonstrated on the measured forced pitch oscillation data. Extensions of the separation techniques to yawing and rolling motions are discussed. In addition, the possibility of considering the angles of attack and sideslip state vector elements as distributed quantities, rather than point quantities, is introduced.
Keywords:
Aircraft Stability and Control
Type:
AIAA Paper 2004-0015
,
42nd AIAA Applied Aerospace Sciences Conference and Exhibit; Jan 05, 2004 - Jan 08, 2004; Reno, NV; United States
Format:
application/pdf
