Aerospace, Defense and Mechanical Engineering

Biography

Biography: Tahura Shahid

Abstract

In order to evaluate the applicability and efficacy of two distinct induced drag computational techniques based upon linearized, attached potential flow theory, a generic trapezoidal wing is analyzed. These two techniques are extensively utilized in academia and aerospace industry and are founded upon vortex lattice method and higher order panel method respectively. An extended VLM-based technique approximates the three dimensional wing and fuselage into a co-planar geometry. Moreover suction parameter that is calculated analytically, is given as an input to capture three dimensional leading edge thrust and vortex lift effects. On the contrary, the higher order panel method, models the complete geometry. It varies the wake orientation with angle of attack, to better predict the effects of downwash. Both techniques incorporate compressibility effects and therefore are more apt to analyze, both subsonic and supersonic regimes. Due to its wide spread applications in conceptual design and optimization of aircraft geometry, these two methods are compared for accuracy, set-up time and input controllability. A wing geometry with identical boundary conditions, flow parameters and number of panels or networks is examined through both the techniques. The pressure distribution thus obtained, is then plotted and results are compared with wind tunnel and CFD data. This comparison concludes the most favorable flow solving technique that better predicts inviscid aerodynamics accurately and efficiently