Meteorologically Induced Variability of Sonic Boom of a Supersonic Aircraft in Cruising or Acceleration Phase

2006 ◽  
Author(s):  
François Coulouvrat
Keyword(s):  
Sonic Boom ◽  
Acceleration Phase ◽  
Supersonic Aircraft

Meteorological Parameters Affecting Supersonic Transport Operations

1967 ◽  
Vol 20 (1) ◽  
pp. 53-63 ◽  
Author(s):  
Richard Scherhag ◽  
Gunter Warnecke ◽  
Werner Wehry
Keyword(s):  
Working Group ◽  
Meteorological Parameters ◽  
Sonic Boom ◽  
Atmospheric Ozone ◽  
Atmospheric Conditions ◽  
Atmospheric Parameters ◽  
Free Atmosphere ◽  
Supersonic Transport ◽  
Supersonic Aircraft ◽  
Initial Task

In 1965, following the Eastbourne Conference, the British, French and German Institutes of Navigation formed a Working Group to make a study of the environment in which the supersonic transport will operate and of its implications for the navigation of such aircraft. The Group's initial task has been one of education, largely through discussion of a series of papers submitted to it. Some of the papers considered have already been published in the Journal (Vol. 19) and a further selection is published below. Table I was contributed by Mr. G. E. Beck. The illustrations to these papers have not all been reproduced.1. Atmospheric Conditions. It will be useful to distinguish between different kinds of atmospheric influences on supersonic aircraft operations. They may be classed as follows:(a) Sporadic effects near the ground(b) Sporadic effects in the free atmosphere(c) Effects on sonic boom(d) Effects of atmospheric ozone(e) Permanently effective atmospheric parameters, such as temperature, density and wind.

Reduction of the sonic boom level in supersonic aircraft flight by the method of surface cooling

2013 ◽  
Vol 20 (6) ◽  
pp. 669-678 ◽  
Author(s):  
V. M. Fomin ◽  
V. F. Chirkashenko ◽  
V. F. Volkov ◽  
A. M. Kharitonov
Keyword(s):  
Sonic Boom ◽  
Surface Cooling ◽  
Supersonic Aircraft ◽  
Aircraft Flight

Active sonic boom control

1996 ◽  
Vol 325 ◽  
pp. 1-28 ◽  
Author(s):  
Steven C. Crow ◽  
Gene G. Bergmeier
Keyword(s):  
Acoustic Waves ◽  
Pressure Field ◽  
Field Approximation ◽  
Simple Relation ◽  
Sonic Boom ◽  
Simulation Code ◽  
Sonic Booms ◽  
Supersonic Aircraft ◽  
Velocity Changes ◽  
Algebraic Term

A theory and simulation code are developed to study non-steady sources as means to control sonic booms of supersonic aircraft. A key result is that the source of sonic boom pressure is not confined to the length of the aircraft but occupies an extensive segment of the flight path. An aircraft in non-steady flight functions as a synthetic aperture antenna, generating complex acoustic waves with no simple relation to instantaneous volume or lift distributions.The theory applies linear acoustics to slender non-steady sources but requires no far-field approximation. The solution for pressure contains a term not seen in Whitham's theory for sonic booms of distant supersonic aircraft. The term describes a pressure field that decays algebraically behind the Mach cone and, in the case of steady flight, integrates to a ground load equal to the weight of the aircraft. The algebraic term is separate from those that describe the sonic boom.Two non-steady source phenomena are evaluated: periodic velocity changes (surge), and periodic longitudinal lift redistribution (slosh). Surge can attenuate a sonic boom and covert it into prolonged weak reverberation, but accelerations needed to produce the phenomenon seem too large for practical use. Slosh may be practical and can alter sonic booms but does not, on average, result in boom attenuation. The conclusion is that active sonic boom abatement is possible in theory but maybe not practical.

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