Computational Analysis of a Multistage Nose Spike to Reduce Drag on a Conceptual Supersonic Transport Aircraft

Abstract. Supersonic commercial aircraft have the potential to greatly reduce global travel times, but key challenges, such as high fuel consumption due to increased drag at supersonic speed, remain a barrier to commercial feasibility. In this study, a Concorde-like delta wing aircraft was modelled and analysed using ANSYS Fluent at different Mach numbers, such as Mach 0.8, 1.02,1.5 and 2. During supersonic flight, significant aerodynamic drag is generated primarily due to wave drag. A multi-stage nose spike was designed and tested to reduce the drag. Results indicate that a stage 4 spike reduced the total drag by 4.23% at Mach 1.5, and the Lift to Drag ratio has increased by 3.9%. The simulation results were compared and validated against results from a previous research paper It is recommended that at subsonic speed, the spike be retracted in position 1, position 2 is optimal for transonic speeds, and position 4 performs best at supersonic speeds.