Computational Fluid Dynamics Studies of a Flapping Wing Nano Air Vehicle (NAV)

Abstract

Standard Form 298 (Rev. 8-98)Prescribed by ANSI Std. Z39.18Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing this collection of information. Flapping wing Nano air vehicle PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) SPONSOR / MONITOR'S ACRONYM(S) 9. SPONSORING / MONITORING AGENCY NAME(S) AND ADDRESS(ES) SPONSOR / MONITOR'S REPORT NUMBER(S)The goal of this project is to develop a Nano Air Vehicle (NAV) with a wing span of 7.5 cm. The computational fluid dynamics study is focused on the aerodynamic efficiency of the wings. The primary focus of the computational study is on the aerodynamic performance of the wings in order to obtain a near optimal kinematics of the wing while the NAV is in a hover mode. The secondary effort was of a more fundamental nature, in order to understand the differences between a rotating helicopter blade and a similarly designed wing undergoing a flapping motion. 31-12-2008Memorandum Report