Staged Aft Body for Alleviation of Tail Boom

Toyoda, Atsushi; Suzuki, Kakuei; Imaizumi, Tsutomu; Sasoh, Akihiro

doi:10.2514/1.j052518

Cited by 5 publications

(6 citation statements)

References 16 publications

(17 reference statements)

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Near-field pressure measurement http://dx.doi.org/10.1016/j.measurement.2015.01.031 0263-2241/Ó 2015 Elsevier Ltd. All rights reserved. experiments in ballistic range facilities contribute a demonstration of sonic boom reduction techniques [15,16].…”

Section: Introductionmentioning

confidence: 99%

Validation of measurement accuracy for near-field pressure around supersonic projectiles in a ballistic range

2015

View full text Add to dashboard Cite

Section: Introductionmentioning

confidence: 99%

Validation of measurement accuracy for near-field pressure around supersonic projectiles in a ballistic range

2015

View full text Add to dashboard Cite

“…In a previous study, 5) a proof-of-concept experiment was performed for a new method for mitigating tail boom, which is based on a "staged aftbody." Each stage of a circular cylinder was followed by a slope generated by a conical contraction, which was then connected to the next stage.…”

Section: Introductionmentioning

confidence: 99%

Low-Boom Performance Demonstration of a Long, Staged Aftbody

Toyoda

Suzuki

Imaizumi

et al. 2015

Trans. Japan Soc. Aero. S Sci.

Self Cite

View full text Add to dashboard Cite

The effectiveness of a "staged aftbody" proposed by Toyoda et al. (AIAA J., Vol. 52, 2014, pp. 2899-2901 was further investigated using an aeroballistic range with a free-flight Mach number of 1.7. Near-field pressure signatures were obtained from a pressure transducer that was flush-mounted on a flat plate. From these signatures, far-field pressure signatures were obtained by the waveform parameter method. It was demonstrated that a flight model whose length-todiameter ratio was even as high as 21 exhibited considerable elongation of the overall tail-boom pressure signature duration, thereby effectively mitigating the tail boom.

show abstract

Section: Reduction Of Sonic Boom and Optimization Studiesmentioning

confidence: 99%

“…Research by Toyoda et al in 2014 investigated methods for mitigating the effects of the aircraft tail boom by creating an experimental model of an aircraft body consisting of three aft-body stages, with each stage having different diameters [22]. The scale model of the body was created, and Schlieren imaging was used to determine the near-field pressure around the experimental model [22]. Their research aimed to examine the effects of compressible flow, where the expansion fan formed merges closer with the oblique shock waves formed at each stage due to different aft-body stages [22].…”

Section: Reduction Of Sonic Boom and Optimization Studiesmentioning

confidence: 99%

“…The scale model of the body was created, and Schlieren imaging was used to determine the near-field pressure around the experimental model [22]. Their research aimed to examine the effects of compressible flow, where the expansion fan formed merges closer with the oblique shock waves formed at each stage due to different aft-body stages [22].…”

Section: Reduction Of Sonic Boom and Optimization Studiesmentioning

confidence: 99%

See 1 more Smart Citation

Reduction of Sonic Boom Loudness Level in Supersonic Aircraft by Optimization of Wing Geometry and Positioning

Tamayo¹

View full text Add to dashboard Cite

Studying the sonic boom phenomenon is an ongoing interest for researchers and engineers to ensure the possibility of supersonic flights for civil aircraft, allowing faster air travel for everyone. Research in sonic boom reduction was previously done by general aircraft shape optimization and engine design. This research focuses on wing geometry modification and its effects on sonic boom loudness reduction. A supersonic aircraft based on the supersonic airliner concept (SSA) was created to learn how the sonic boom loudness and overpressures change by applying wing geometry sensitivity analyses. The sensitivity analyses include wing geometry changes, wing sweep angle changes, and wing translation while maintaining the same aircraft lift. The volume of the selected aircraft is then matched to the base SSA model for geometric parity. A 2.88 PLdB reduction in sonic boom loudness was achieved while maintaining the same volume and lift as the base SSA model. i I am deeply thankful for the support and encouragement given to me by my supervisor Dr. Joana Rocha, whose research supervision and guidance allowed me to progress this research to completion step-by-step without too much stress. I am grateful for Dr. Rocha's kindness and constant support throughout the difficult times of the Covid-19 pandemic, helping me overcome my sadness and stress of the earlier times during the pandemic. I would also like to thank my family, especially my mother and father, whose constant support and love motivated me to finish this research during difficult times. Despite being overseas, they never forgot to keep in touch and encourage me through my journey to finishing this research.

show abstract

Staged Aft Body for Alleviation of Tail Boom

Cited by 5 publications

References 16 publications

Validation of measurement accuracy for near-field pressure around supersonic projectiles in a ballistic range

Validation of measurement accuracy for near-field pressure around supersonic projectiles in a ballistic range

Low-Boom Performance Demonstration of a Long, Staged Aftbody

Reduction of Sonic Boom Loudness Level in Supersonic Aircraft by Optimization of Wing Geometry and Positioning

Contact Info

Product

Resources

About