Conceptual Design of a D8 Commercial Aircraft

Yutko, Brian; Titchener, Neil; Courtin, Christopher; Lieu, Michael; Wirsing, Larry; Tylko, J.; Chambers, Jeffrey T.; Roberts, T.; Church, Clinton S.

doi:10.2514/6.2017-3590

Cited by 30 publications

(25 citation statements)

References 9 publications

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“…The NASA D8 concept is based on the Massachusetts Institute of Technology (MIT)/Aurora Flight Sciences D8 aircraft first developed under a 2008 NASA Research Announcement [1] and later updated by Drela [2]. Yutko et al [3] undertook a comprehensive conceptual design of the MIT/Aurora D8. The AATT project has independently evaluated the D8 concept for several years.…”

Section: Introductionmentioning

confidence: 99%

“…A noncylindrical fuselage experiences additional stresses and bending moments while under pressure, which necessitates structural reinforcements that can be heavy and expensive. The ND8 features a twin-aisle lifting body fuselage [3]. This "double-bubble" design retains a similar load path through the fuselage structure by using two partial cylinders braced with faired tension rods in the cabin [5].…”

Section: Introductionmentioning

confidence: 99%

“…This design enables a wide fuselage, which leads to increased passenger capacity, faster boarding times, and a certain amount of lift generated by the fuselage. The lift generated by the fuselage has several impacts on the design of the airframe, namely the reduction of wing area in proportion to the size of the fuselage, and a decrease of horizontal tail area due to the increased lift acting near the front of the aircraft, which contributes a positive pitching moment [3].…”

Section: Introductionmentioning

confidence: 99%

“…The effect of incorporating boundary layer ingestion was limited to increased shielding with the engines placed at the aft dorsal location. A full conceptual design of the Aurora/MIT D8 also featured a noise assessment [3]. Boundary layer ingestion was incorporated into the design, and noise was predicted with and without this feature.…”

Section: Introductionmentioning

confidence: 99%

“…The configuration change to shift the engines from the underwing location (no BLI) to the aft dorsal location (to enable BLI) is reported to provide a noise reduction of approximately 7 EPNdB on a system level. It is assumed by the authors of this study that Yutko et al [3] computed the acoustic BLI effect considering only the system benefits associated with reduced engine requirements, reduced weight, and favorable placement of the engines above the fuselage to take advantage of noise shielding. Prior experiments have shown that boundary layer ingestion, and inflow distortion in general, leads to significantly increased fan noise due to unsteady loading of the fan blades [9][10][11].…”

Section: Introductionmentioning

confidence: 99%

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Aircraft System Noise Assessment of the NASA D8 Subsonic Transport Concept

Clark

Thomas

Guo³

2018

2018 AIAA/CEAS Aeroacoustics Conference

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A vehicle-level noise assessment has been performed for the NASA D8 concept aircraft (ND8) in the NASA Advanced Air Transport Technology Project portfolio. The NASA research-level Aircraft NOise Prediction Program (ANOPP-Research) was used to predict the noise from each source component on the ND8 to build up a noise estimate for the full aircraft. The propulsion airframe aeroacoustic (PAA) effects of the ND8, namely boundary layer ingestion (BLI) with its influence on fan noise, and the noise shielding, reflection, and diffraction mechanisms of the unconventional airframe, were empirically modeled using experimental data. Noise reduction technologies appropriate to the 2025-2035 time frame were included in this study. Including all technologies and PAA effects, the ND8 is predicted to have a cumulative margin to the Stage 4 certification metric of only 7.4 EPNdB. Boundary layer ingestion is predicted to have a detrimental impact on cumulative noise levels on the order of 15 EPNdB. Fan noise is seen to be the primary noise source at all three certification points, even if the BLI noise impact could be entirely suppressed. The impact of engine noise shielding by the airframe is limited by a lack of aft shielding and the presence of horizontal tail reflections in the aft direction. The physical constraint on engine size by the pi-tail is seen as a potential barrier to engine noise reduction through the corresponding limitation on fan bypass ratio. Mildly reduced climb performance (compared to similar reference aircraft) does not provide any benefit through increased noise propagation distance. If the boundary layer ingestion noise penalty could be suppressed such that BLI would have no effect on noise, the cumulative margin to Stage 4 would increase to 22.4 EPNdB, still below the NASA Mid Term goal of 32-42 EPNdB.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

Aircraft System Noise Assessment of the NASA D8 Subsonic Transport Concept

Clark

Thomas

Guo³

2018

2018 AIAA/CEAS Aeroacoustics Conference

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Advanced low-noise aircraft configurations and their assessment: past, present, and future

Spakovszky

2019

CEAS Aeronaut J

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Performance bookkeeping for aircraft configurations with fuselage wake-filling propulsion integration

et al. 2019

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The aim of this research is the identification of a unified bookkeeping and evaluation scheme for the integrated performance analysis of a boundary layer ingesting (BLI) concept in the conceptual design phase. A thorough review and classification of existing performance bookkeeping schemes suits as a basis for the derivation of a bookkeeping scheme suitable for the initial sizing as well as detailed design analysis during the conceptual phase of a BLI concept. Figures of merit for the concept performance assessment are evaluated with regard to the requirements of aircraft multidisciplinary conceptual design. Based on the survey, the most practical integral momentum conservation approach is deduced and its application to integrated conceptual sizing and a subsequent design analysis is evaluated. The proposed scheme is universally applicable to coupled airframe-propulsion aircraft concepts, compatible with standard aircraft and propulsion system sizing tools and, under certain assumptions, deployable for low-and high-fidelity evaluation methods. Finally, several figures of merit are selected to cover a range of design aspects in the BLI evaluation.

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Conceptual Design of a D8 Commercial Aircraft

Cited by 30 publications

References 9 publications

Aircraft System Noise Assessment of the NASA D8 Subsonic Transport Concept

Aircraft System Noise Assessment of the NASA D8 Subsonic Transport Concept

Advanced low-noise aircraft configurations and their assessment: past, present, and future

Performance bookkeeping for aircraft configurations with fuselage wake-filling propulsion integration

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