A vortex-lattice method for calculating longitudinal dynamic stability derivatives of oscillating delta wingsA nonsteady vortex-lattice method is introduced for predicting the dynamic stability derivatives of a delta wing undergoing an oscillatory motion. The analysis is applied to several types of small oscillations in pitch. The angle of attack varied between + or - 1 deg, with the mean held at 0 deg when the flow was assumed to be attached and between + or - 1 deg and the mean held at 15 deg when both leading-edge separation and wake roll-up were included. The computed results for damping in pitch are compared with several other methods and with experiments, and are found to be consistent and in good agreement.
Document ID
19810060166
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Levin, D. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 11, 2013
Publication Date
August 1, 1981
Subject Category
Aircraft Stability And Control
Report/Patent Number
AIAA PAPER 81-1876
Meeting Information
Meeting: Atmospheric Flight Mechanics Conference
Location: Albuquerque, NM
Start Date: August 19, 1981
End Date: August 21, 1981
Sponsors: American Institute of Aeronautics and Astronautics