Improved drag prediction using mach-cone influence in vortex lattice method for supersonic aircraft

This work is a development of a low-order solver for the next generation of supersonic aircraft preliminary design that simplifies the numerical models and reduces the computational costs associated with high-fidelity simulations. To improve the accuracy of drag prediction for supersonic flow, a combined use of the Taylor MacColl hypervelocity method (TMHM) with the supersonic vortex lattice method is proposed to model the machcone influence on the vortex lattice method. This involves a panel matching technique computing lift and drag forces for n number of panels from VLM and using TMHM to calculate the wave drag and skin friction drag. The combination of these methods allows for an improved prediction of the total drag of the body in supersonic flow for the low-order method approach. The results are compared with experimental data to validate the accuracy of the combined method. To validate the accuracy of our combined method, extensive comparisons with experimental data are conducted. Quantitatively, the results reveal a remarkable 20% reduction in drag prediction error for supersonic flows compared to the conventional vortex lattice method. This substantial improvement positions this solver as a highly accurate and efficient tool for the design and optimization of supersonic vehicles. In summary, our research underscores the computational advantages of this integrated approach, emphasizing its quantitative gains in accuracy, particularly in the challenging context of shockwave interactions.