The objective of this study was to outline an approach for the quantification of uncertainty in sonic boom measurements and to investigate the effect of various near-field uncertainty representation approaches on ground noise predictions. These approaches included a symmetric versus asymmetric uncertainty band representation and a dispersion technique based on a partial sum Fourier series that allows for the inclusion of random error sources in the uncertainty. The near-field uncertainty was propagated to the ground level, along with additional uncertainty in the propagation modeling. Estimates of perceived loudness were obtained for the various types of uncertainty representation in the near-field. Analyses were performed on three configur...
The acoustic propagation stage of a computational aeroacoustic analysis has been in- vestigated for ...
The Sonic Boom Simulator of the Langley Research Center was used to quantify subjective loudness res...
Two F-18 aircraft were flown, one above the other, in two formations, in order for the shock systems...
As the state of the art in uncertainty quantification for low-boom aircraft advances, the underlying...
Aircraft sonic boom characteristics predicted from near field data obtained in wind tunne
Near-field pressure signatures were measured and computational predictions made for several sonic bo...
The purpose of this paper is to investigate the noise generation of a low-boom aircraft design in fl...
The primary objective of this work was to develop and demonstrate a process for accurate and efficie...
Dassault Aviation as a civil aircraft manufacturer is studying the feasibility of a supersonic busin...
Intrinsic variability due to micrometeorological effects and/or ground effects, measurement uncertai...
The topics discussed include the following: atmospheric turbulence; BOOMFILE Database description; B...
International audienceA comparison of sonic boom propagation codes from NASA and ONERA was conducted...
As the industry progresses towards realizing a commercial supersonic aircraft, the push to reduce no...
A careful study is conducted to assess the numerical mesh resolution requirements for the accurate c...
Aircraft system level noise prediction for advanced, unconventional concepts has undergone significa...
The acoustic propagation stage of a computational aeroacoustic analysis has been in- vestigated for ...
The Sonic Boom Simulator of the Langley Research Center was used to quantify subjective loudness res...
Two F-18 aircraft were flown, one above the other, in two formations, in order for the shock systems...
As the state of the art in uncertainty quantification for low-boom aircraft advances, the underlying...
Aircraft sonic boom characteristics predicted from near field data obtained in wind tunne
Near-field pressure signatures were measured and computational predictions made for several sonic bo...
The purpose of this paper is to investigate the noise generation of a low-boom aircraft design in fl...
The primary objective of this work was to develop and demonstrate a process for accurate and efficie...
Dassault Aviation as a civil aircraft manufacturer is studying the feasibility of a supersonic busin...
Intrinsic variability due to micrometeorological effects and/or ground effects, measurement uncertai...
The topics discussed include the following: atmospheric turbulence; BOOMFILE Database description; B...
International audienceA comparison of sonic boom propagation codes from NASA and ONERA was conducted...
As the industry progresses towards realizing a commercial supersonic aircraft, the push to reduce no...
A careful study is conducted to assess the numerical mesh resolution requirements for the accurate c...
Aircraft system level noise prediction for advanced, unconventional concepts has undergone significa...
The acoustic propagation stage of a computational aeroacoustic analysis has been in- vestigated for ...
The Sonic Boom Simulator of the Langley Research Center was used to quantify subjective loudness res...
Two F-18 aircraft were flown, one above the other, in two formations, in order for the shock systems...