Lessons Learned-Quiet SpikeTM Flight Test Program

Freund, Donald; Simmons, Frank; Howe, D.; Cowart, Robbie; Grindle, Tom

doi:10.2514/6.2008-130

Cited by 6 publications

(2 citation statements)

References 9 publications

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“…The Shaped Sonic Boom Demonstration (SSBD) project 2 demonstrated in flight that the bow shock could be shaped and significantly attenuated by careful shaping of the fore body of a modified F-5E aircraft (Northrop Corporation, now Northrop Grumman Corporation). The Gulfstream Quiet Spike™ project 3 (Gulfstream Aerospace Corporation, A General Dynamics Company, Savannah, Georgia) evaluated the structural dynamic characteristics of a shaped telescoping boom that extended out of the forward fuselage of a NASA F-15B aircraft (McDonnell Douglas Corporation, now The Boeing Company) and provided near-field pressure measurements of the boom in flight.…”

Section: Introductionmentioning

confidence: 99%

CFD Analysis of the Nozzle Jet Plume Effects on Sonic Boom Signature

Bui

2009

47th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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An axisymmetric full Navier-Stokes computational fluid dynamics study is conducted to examine nozzle exhaust jet plume effects on the sonic boom signature of a supersonic aircraft. A simplified axisymmetric nozzle geometry, representative of the nozzle on the NASA Dryden NF-15B Lift and Nozzle Change Effects on Tail Shock research airplane, is considered. The computational fluid dynamics code is validated using available wind-tunnel sonic boom experimental data. The effects of grid size, spatial order of accuracy, grid type, and flow viscosity on the accuracy of the predicted sonic boom pressure signature are quantified. Grid lines parallel to the Mach wave direction are found to give the best results. Second-order accurate upwind methods are required as a minimum for accurate sonic boom simulations. The highly underexpanded nozzle flow is found to provide significantly more reduction in the tail shock strength in the sonic boom N-wave pressure signature than perfectly expanded and overexpanded nozzle flows. A tail shock train in the sonic boom signature is observed for the highly underexpanded nozzle flow. Axisymmetric computational fluid dynamics simulations show the flow physics inside the F-15 nozzle to be nonisentropic and complex. Although the one-dimensional isentropic nozzle plume results look reasonable, they fail to capture the sonic boom shock train in the highly underexpanded nozzle flow. Nomenclature

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Section: Introductionmentioning

confidence: 99%

CFD Analysis of the Nozzle Jet Plume Effects on Sonic Boom Signature

Bui

2009

47th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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“…Gulfstream and NASA cooperated in the flight trails which aimed to test the effect of the Quiet Spike in sonic boom mitigation. The Quiet Spike was adapted to an F-15B flight research aircraft, and a total of 32 research flights were conducted [218][219][220]. The Quiet Spike has been shown to be capable of achieving a 0.2 psf initial shock reduction and an increase of 25% in rise time [216].…”

Section: Nose Spikementioning

confidence: 99%

Review of Sonic Boom Prediction and Reduction Methods for Next Generation of Supersonic Aircraft

Bonavolontà,

Lawson,

Riaz

2023

Aerospace

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The reduction of sonic boom levels is the main challenge but also the key factor to start a new era of supersonic commercial flights. Since 1970, a FAA regulation has banned supersonic flights overland for unacceptable sonic booms at the ground, and many research studies have been carried out from that date to understand sonic boom generation, propagation and effects, both on the environment and communities. Minimization techniques have also been developed with the attempt to reduce sonic boom annoyance to acceptable levels. In the last 20 years, the advances in both knowledge and technologies, and companies and institutions’ significant investments have again raised the interest in the development of new methods and tools for the design of low boom supersonic aircraft. The exploration of unconventional configurations and exotic solutions and systems seems to be needed to effectively reduce sonic boom and allow supersonic flight everywhere. This review provides a description of all aspects of the sonic boom phenomenon related to the design of the next generation of supersonic aircraft. In particular, a critical review of the prediction and minimization methods found in the literature, aimed at identifying their strengths, limitations and gaps, is made, along with a complete overview of disruptive unconventional aircraft configurations and exotic active/passive solutions to boom level reduction. The aim of the work is to give a clear statement of state-of-the-art sonic boom prediction methods and possible reduction solutions to be explored for the design of next low-boom supersonic aircraft.

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Review and prospect of supersonic business jet design

Sun

Smith

2017

Progress in Aerospace Sciences

106

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This paper reviews the environmental issues and challenges appropriate to the design of supersonic business jets (SSBJs). There has been a renewed, worldwide interest in developing an environmentally friendly, economically viable and technologically feasible supersonic transport aircraft. A historical overview indicates that the SSBJ will be the pioneer for the next generation of supersonic airliners. As a high-end product itself, the SSBJ will likely take a market share in the future. The mission profile appropriate to this vehicle is explored considering the rigorous environmental constraints. Mitigation of the sonic boom and improvements aerodynamic efficiency in flight are the most challenging features of civil supersonic transport. Technical issues and challenges associated with this type of aircraft are identified, and methodologies for the SSBJ design are discussed. Due to the tightly coupled issues, a multidisciplinary design, analysis and optimization environment is regarded as the essential approach to

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Lessons Learned-Quiet SpikeTM Flight Test Program

Cited by 6 publications

References 9 publications

CFD Analysis of the Nozzle Jet Plume Effects on Sonic Boom Signature

CFD Analysis of the Nozzle Jet Plume Effects on Sonic Boom Signature

Review of Sonic Boom Prediction and Reduction Methods for Next Generation of Supersonic Aircraft

Review and prospect of supersonic business jet design

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