Numerical Simulations of a Quiet SuperSonic Technology (QueSST) Aircraft Preliminary Design

Recent efforts to optimize aircraft for drag and loudness have yielded point-designs, which produce the optimal drag and loudness for a specific flight condition [1-3]. When flown at a different flight condition, the aircraft can experience significant increases in loudness or drag depending on the changes in flight and atmospheric conditions. The NASA University Leadership Initiative (ULI) program titled "Adaptive Aerostructures for Revolutionary Civil Supersonic Transportation" (hereafter referred to as "the ULI program") has focused its efforts on expanding the optimal flight envelope of supersonic aircraft through changing the outer mold line (OML) of the aircraft using shape-memory alloys (SMAs). By making small changes or deformations to an aircraft geometry, it has been found that sonic boom loudness can be decreased for off-design flight conditions [4, 5]. Predicting sonic boom loudness follows the procedure outlined in Fig. 1. First, a description of the OML of the aircraft geometry is defined, which is then used in an aerodynamic model to measure pressure perturbations at some radial distance from the center-line of the body. The pressure perturbations are represented in the form of a near-field pressure signature. In three-dimensions, the pressure perturbations create a near-field pressure cone around the aircraft that can be sampled at various azimuthal angles to obtain the slice shown in Fig. 1.

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Numerical Simulations of a Quiet SuperSonic Technology (QueSST) Aircraft Preliminary Design

Cited by 3 publications

References 8 publications

UNS3D Near-Field Predictions for the Third AIAA Sonic Boom Prediction Workshop

UNS3D Near-Field Predictions for the Third AIAA Sonic Boom Prediction Workshop

A Multi-Fidelity Prediction of Aerodynamic and Sonic Boom Characteristics of the JAXA Wing Body

Near-field Pressure Signature Splicing for Low-Fidelity Design Space Exploration of Supersonic Aircraft

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