scholarly journals Application of thermoanemometric measurements in studies of near field of sonic boom

2017 ◽  
Author(s):  
T. A. Kiseleva
Keyword(s):  
Near Field ◽  
Sonic Boom

scholarly journals Specialized CFD Grid Generation Methods for Near-Field Sonic Boom Prediction

2014 ◽  
Author(s):  
Michael A. Park ◽  
Richard L. Campbell ◽  
Alaa A. Elmiligui ◽  
Susan E. Cliff ◽  
Sudheer Nayani
Keyword(s):  
Near Field ◽  
Grid Generation ◽  
Sonic Boom

scholarly journals Efficient Near-Field to Mid-Field Sonic Boom Propagation Using a High-Order Space Marching Method

2019 ◽  
Author(s):  
Jeffrey A. Housman ◽  
Gaetan K. Kenway ◽  
James C. Jensen ◽  
Cetin C. Kiris
Keyword(s):  
Near Field ◽  
High Order ◽  
Sonic Boom ◽  
Marching Method

Numerical study of the of sonic boom near-field

2019 ◽  
Author(s):  
P. A. Mishchenko ◽  
T. A. Kiseleva
Keyword(s):  
Numerical Study ◽  
Near Field ◽  
Sonic Boom

Euler code prediction of near-field to midfield sonic boom pressure signatures

1993 ◽  
Vol 30 (6) ◽  
pp. 911-917 ◽  
Author(s):  
M. J. Siclari ◽  
C. M. Darden
Keyword(s):  
Near Field ◽  
Sonic Boom

scholarly journals Sonic Boom Calculations in the Near Field.

1993 ◽  
Vol 41 (477) ◽  
pp. 584-589 ◽  
Author(s):  
Akihiko YOSHIDA ◽  
Kazuhiro NAKAHASHI ◽  
Shoichi FUJII
Keyword(s):  
Near Field ◽  
Sonic Boom

scholarly journals To the issue of evaluating sonic boom overpressure and loudness

2019 ◽  
Vol 304 ◽  
pp. 02003
Author(s):  
Igor G. Bashkirov ◽  
Sergey L. Chernyshev ◽  
Vladlen S. Gorbovskoy ◽  
Andrey V. Kazhan ◽  
Vyacheslav G. Kazhan ◽  
...  
Keyword(s):  
Software Package ◽  
Stokes Equations ◽  
Aerodynamic Drag ◽  
Near Field ◽  
Theoretical Data ◽  
Aerodynamic Characteristics ◽  
Sonic Boom ◽  
Navier Stokes ◽  
Navier Stokes Equations ◽  
Computational Mesh

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).

Effects of Atmospheric Uncertainties on Sonic Boom Perceived Level

2021 ◽  
Vol 143 (4) ◽  
Author(s):  
Sohail R. Reddy ◽  
Janhavi Chitale ◽  
George S. Dulikravich
Keyword(s):  
Polynomial Chaos ◽  
Burgers Equation ◽  
Near Field ◽  
Three Dimensional ◽  
Sonic Boom ◽  
Temperature Profiles ◽  
Sonic Booms ◽  
Highly Sensitive ◽  
Atmospheric Profiles ◽  
Wind Profiles

Abstract This work quantifies the uncertainty in Stevens Mark VII Perceived Level of sonic booms due to uncertainties in atmospheric profiles. The influence of temperature, humidity, and wind profiles, at six cities around the globe, on the sonic boom loudness is calculated. The flow field around an aircraft was obtained by solving the three-dimensional (3D), compressible Euler equations using the UNS3D solver. The near-field pressure signature is then propagated through the atmosphere by solving the augmented Burgers equation using the sBOOM solver. The uncertainty is modeled using a nonintrusive polynomial chaos approach. A sensitivity analysis is performed to identify the altitude range and the atmospheric variable to which the Perceived Level is most sensitive. It was shown that the Perceived Level is not sensitive to any particular altitude but rather the atmospheric profiles. It was also seen that the Perceived Level is highly sensitive to humidity and temperature profiles and less sensitive to the wind profiles.

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