Optimum flight parameters and stability computations using continuation technique

Abstract

Illustrative examples are presented in this paper to show the applications of the continuation-algorithm-based, recently developed extended bifurcation analysis (EBA) methodology to compute optimum flight parameters of an F/A-18 high-angle-of-attack research vehicle aerodynamic model. A complete model describing the six-degree-of-freedom motion of aircraft is used in this analysis to compute trims for the aircraft in constrained flights, for example, straight and level and steady climb flights. Using the results of such computations, one can plot the performance curves for aircraft which are in contrast to the performance curves usually available in the aircraft design text books. Special features of the performance curves computed here are high-lighted and the reasons for the contrasting features between the performance curves obtained here and the corresponding ones presented in the aircraft design text books are discussed. Primary objective of this work is to show the efficiency of the EBA methodology in evaluating the optimum values of multiple objective functions which usually requires the use of the optimization theory-based numerical techniques and can be generally computationally exhaustive in terms of time and efforts.