Computational fluid dynamics (CFD) is having an increasing impact on the aerodynamic assessment of air vehicles, and a large number of codes employing a variety of solution strategies are now available. However, before a code can be used with confidence it is advisable to evaluate its predictive performance by comparing results with reliable experimental data. The aim is to compare results from a new CFD solver with data from a series of wind tunnel experiments, carried out specifically to provide a comprehensive set of experimental data for the evaluation of CFD methods for missiles.
The project will focus on two configurations from the experimental database, both based on the same axisymmetric body with and without wings at M=2.5 and AoA=14. These test cases have been studied extensively in the past and are well established and understood.
Experimental force and moment data, surface pressures and flowfield surveys were originally obtained at DERA Bedford. Additional wind tunnel tests were completed at the NASA Langley Research Center, during which additional force and moment data were acquired, along with vapour screen, schlieren and oil flow images.
The project will look at different meshing strategies, numerical schemes and turbulence models.