This paper first describes the numerical simulation and shape optimization of the Lockheed SEEB-ALR and 69 Degree Delta Wing-Body for computing the sonic boom signature in the nearfield and its minimization using a genetic algorithm. Then the propagation of sonic boom in the atmosphere is simulated all the way to the ground for both the original and optimized body shapes. For flow field calculation, the commercial CFD flow solver ANSYS Fluent is employed. The near field pressure disturbance is used to determine the strength of the sonic boom signature. The computational results for the two cases are compared with the experimental data. The body shapes are then optimized using a single-objective genetic algorithm. The results show a significant decrease in strength of the sonic boom. The pressure data from these two models is then scaled and propagated through the atmosphere using the NASA Langley Research Center sBOOM code to predict the far field signature of these bodies at the scale of a commercial supersonic aircraft.

Document Type

Final Report

Author's School

School of Engineering and Applied Science

Author's Department

Mechanical Engineering and Materials Science

Class Name

Mechanical Engineering and Material Sciences Independent Study

Date of Submission