Optimal Wave Drag Reduction Technique for Fighter Aircraft Using von Kármán Ogive and Haack Series
Abstract
In the supersonic regime, total drag rises colossally at higher speeds due to shockwaves. Drag reduction is
imperative for modern fighter aircraft to efficiently sustain higher Mach during flight. Hence, various techniques are integrated into the preliminary design phase enabling these modern fighter aircraft to super-cruise. Area ruling leads to better high-speed aerodynamic performance. Utilizing the Sears-Haack cross-sectional area ruling techniques is one of the drag-minimization processes. Various Haack series are explored in this study for a wing-body configuration to analyse the methodology that can be applied for the design of a modern multi-role fighter aircraft ensuring the required aircraft volume is conserved. Application of Von Kármán integral equation leads to better optimization of fuselage shape and hence impart a significant effect on supersonic drag. Employing this phenomenon, in the following research, decreased wave drag by 45% at Mach 1.0. Other Haack series can provide better results but the implementation is limited by the area of application. Therefore, the selection of methodology applied for the enhancement of supercruise capability is the key finding of this study.
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