NUMERICAL INVESTIGATION OF FLOW AROUND SPIT FIRE Mk VIII AIRCRAFT

Casestudy No: FTLCFD202301

Introduction

Accurate and cost-effective Computational Fluid Dynamics (CFD) methods, coupled with easy access to computational resources and numerical modeling tools, play a vital role in optimizing fighter aircraft. This benchmark study focuses on assessing flow patterns and pressure distributions around the legendary SPITFIRE Mk VIII in low subsonic, incompressible flow conditions.
The SPITFIRE, designed by Reginald Mitchell and produced by Supermarine Aviation Works, is an iconic British fighter aircraft renowned for its pivotal role in World War II. Its sleek, streamlined design, featuring elliptical wings, contributed to its exceptional maneuverability and high-speed performance.

Figure1: SPIT FIRE Mk VIII Fighter Aircraft [1]

The flow conditions used for benchmarking are Mach number M = 0.26, Angle of Attack = 8 degrees, Inlet velocity V = 90 m/sec and Pressure P = 0 Pa gauge pressure at outlet. For turbulence modelling, k-omega SST model was used with the wall function approach. 

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