Abstract
At present, in the world there is a growing interest in the development of a new generation of supersonic passenger aircraft. One of the main problems of creating such aircraft is to ensure both an acceptable sonic boom level and high aerodynamic characteristics in the supersonic cruising mode. This requires the development of reliable methods for obtaining the near field under the plane with taking into account the influence of the boundary layer, calculation of overpressure signature on the ground and evaluation of sonic boom loudness. In this work four variants of the equivalent body of revolution of minimum sonic boom with different nose sharpening were investigated for an aircraft weighing 19 tons in supersonic cruising flight at Mach number of 1.7 and altitude of 15.5 km using the software package for solving the Reynolds–averaged Navier–Stokes equations (RANS) ANSYS CFX. A macro for calculating the overpressure signature on the ground for the distribution of disturbances in the near field under the aircraft and a program for evaluating the sonic boom loudness in various metrics were developed. Computational mesh verification of the results was carried out, the obtained overpressure signatures were compared with theoretical data and calculation results from the software package for the integration of complete system of Euler equations by finite–difference method X–CODE. The effect of the sharpening of the nose part on aerodynamic drag and sound boom characteristics was shown. The work was done in the interests of the international project RUMBLE (RegUlation and norM for low sonic Boom LEvels).
Highlights
One of the challenges of modern aviation science is a creation of the new generation civil supersonic transport (SST), which can significantly reduce the flight time and increase the one-day travel range up to 7000-8000 km
It is possible to take into account the real atmospheric parameters, such as humidity, temperature, wind, etc. - The loudness of the signal that came to the ground is calculated taking into account the acoustical reflection from the ground by means of Fourier transform with further correction of the spectrum according to the chosen metrics
Creation of the new generation of civil supersonic aircraft requires adopting of international standards and developing technical solutions to ensure the reduction to acceptable levels of sonic boom and airport noise, aerodynamic and weight efficiency, etc
Summary
One of the challenges of modern aviation science is a creation of the new generation civil supersonic transport (SST), which can significantly reduce the flight time and increase the one-day travel range up to 7000-8000 km. Under the auspices of ICAO, work is underway to create standards for an acceptable level of sonic boom and noise near the airport for perspective supersonic passenger aircraft (NASA and Lockheed Martin QueSST projects [1], JAXA D-SEND [2], the European Union and Russia RUMBLE [3]) These projects are aimed at determining the level of impact of sonic boom of various intensity on the environment, people, buildings and structures, including the use of low-boom technology demonstrators, and at developing computational methods to predict the propagation of sonic boom in real atmosphere [4]. The example of equivalent bodies of revolution of minimum sonic boom shows the effect of sharpening of the body nose on the aerodynamic drag characteristics and sonic boom intensity is shown
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