Citation

Chen DH, Wu WH, Wang JJ, Huang Y. Aeronaut. J. 2007; 111(1120): 373-380.

Affiliation

Beijing University of Aeronautics and Astronautics (BUAA), Beijing, China

Copyright

(Copyright © 2007, Royal Aeronautical Society, Publisher Cambridge University Press)

DOI

unavailable

PMID

unavailable

Abstract

A unique experimental method is used, in combination with numerical calculation and engineering estimation, to study the aerodynamic performance of an ejection seat at M = 0-60, 0-90 and 1-20, angles-of-attack alpha = 0 degrees-360 degrees, and sideslip angles beta= 0 degrees-90 degrees. Several basic characteristics of the aerodynamic performance are explored. The normal force of the ejection seat varies in a sinusoidal way and the axial force in a cosinoidal way, with the angle-of-attack. The model is statically unstable longitudinally at most attitude angles and the longitudinal stability could be improved by a stabiliser. These characteristics result from a large low pressure area caused by the leeward separation and the windward high pressure area in the ejection seat flow field, at all alpha, due to the blunt configuration. A set of engineering calculation formulae is deduced, based on the aerodynamic characteristics of the ejection seat.

Language: en