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Longitudinal Stability Analysis of Business Jet Aircraft

In this research paper the longitudinal stability of a business jet has been discussed. Aircraft has been observed at two different flight conditions (altitudes) at subsonic Mach number. Analysis and estimations have been done in such a way that the aircraft body has been divided into three components i.e. wing, tail and fuselage and contribution of each component towards pitching moment has been determined by using basic equations of aerodynamic moments and stick forces. Total pitching moment and stick fixed neutral point has also been evaluated. The entire analytical methodology has been incorporated into a computer aided worksheet which has provided us with fast and quick results. Graphs have been plotted to proof the validity of calculated results. The verification of the result has also been done using stability analysis software. Individual components have separately been modelled and subsequently analyzed in the software. Achievements made through this research are that findings have confirmed the static longitudinal stability of the business jet aircraft with its tail having the significant static longitudinal stability contribution.