Computational Assessment of the Boundary Layer Ingesting Nacelle Design of the D8 Aircraft

Pandya, Shishir A.; Uranga, Alejandra; Espitia, Alejandro E; Huang, Arthur C.

doi:10.2514/6.2014-0907

Cited by 45 publications

(36 citation statements)

References 10 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…More aggressive fuel burn benefits can be expected from BLI, if larger percentage of boundary layer can be ingested [33,34]. Table 2 summarizes the recent research findings on BLI benefits for commercial aircraft.…”

Section: Boundary Layer Ingestionmentioning

confidence: 99%

“…According to the system study by NASA researchers [31], 3-5% fuel burn benefit can be achieved by BLI technology relative to a clean-inflow, pylon-mounted, advanced Ultra-High Bypass Ratio baseline turbofan engines. More aggressive fuel burn benefits can be expected from BLI, if larger percentage of boundary layer can be ingested [33,34]. Table 2 summarizes the recent research findings on BLI benefits for commercial aircraft.…”

Section: Boundary Layer Ingestionmentioning

confidence: 99%

See 1 more Smart Citation

Exploring Vehicle Level Benefits of Revolutionary Technology Progress via Aircraft Design and Optimization

et al. 2018

View full text Add to dashboard Cite

Abstract:It is always a strong motivation for aeronautic researchers and engineers to reduce the aircraft emissions or even to achieve emission-free air transport. In this paper, the impacts of different game-changing technologies together on the reduction of aircraft fuel consumption and emissions are studied. In particular, a general tool has been developed for the technology assessment, integration and also for the overall aircraft multidisciplinary design optimization. The validity and robustness of the tool has been verified through comparative and sensitivity studies. The overall aircraft level technology assessment and optimization showed that promising fuel efficiency improvements are possible. Though, additional strategies are required to reach the aviation emission reduction goals for short and medium range configurations.

show abstract

Section: Boundary Layer Ingestionmentioning

confidence: 99%

Section: Boundary Layer Ingestionmentioning

confidence: 99%

Exploring Vehicle Level Benefits of Revolutionary Technology Progress via Aircraft Design and Optimization

et al. 2018

View full text Add to dashboard Cite

show abstract

“…More recent studies have combined Boundary-Layer Ingestion technology with blended wing body (BWB) geometry configurations in order to reduce specific fuel consumption for the aircraft [5][6][7] . These studies all show a reduction in the mechanical power required by the propulsor as compared to a typical podded nacelle configuration.…”

Section: Introductionmentioning

confidence: 99%

Computational Investigation of a Boundary Layer Ingestion Propulsion System for the Common Research Model

Blumenthal

Elmiligui

Geiselhart

et al. 2016

46th AIAA Fluid Dynamics Conference

View full text Add to dashboard Cite

The present paper examines potential propulsive and aerodynamic benefits of integrating a Boundary-Layer Ingestion (BLI) propulsion system into a typical commercial aircraft using the Common Research Model (CRM) geometry and the NASA Tetrahedral Unstructured Software System (TetrUSS). The Numerical Propulsion System Simulation (NPSS) environment is used to generate engine conditions for CFD analysis. Improvements to the BLI geometry are made using the Constrained Direct Iterative Surface Curvature (CDISC) design method. Previous studies have shown reductions of up to 25% in terms of propulsive power required for cruise for other axisymmetric geometries using the BLI concept. An analysis of engine power requirements, drag, and lift coefficients using the baseline and BLI geometries coupled with the NPSS model are shown. Potential benefits of the BLI system relating to cruise propulsive power are quantified using a power balance method, and a comparison to the baseline case is made. Iterations of the BLI geometric design are shown and any improvements between subsequent BLI designs presented. Simulations are conducted for a cruise flight condition of Mach 0.85 at an altitude of 38,500 feet and an angle of attack of 2° for all geometries. A comparison between available wind tunnel data, previous computational results, and the original CRM model is presented for model verification purposes along with full results for BLI power savings. Results indicate a 14.4% reduction in engine power requirements at cruise for the BLI configuration over the baseline geometry. Minor shaping of the aft portion of the fuselage using CDISC has been shown to increase the benefit from Boundary-Layer Ingestion further, resulting in a 15.6% reduction in power requirements for cruise as well as a drag reduction of approximately eighteen counts over the baseline geometry.

show abstract

“…BLI leads to increased propulsive efficiency by reducing the flow velocity differential between the propulsive airstream and the free stream flow, compared to a traditional configuration of engines under the wing [6]. Much work has been done on the aerodynamic impact of such a design [6,7] and in designing an "inflow-distortion-tolerant" fan, but the acoustic impact of this configuration has not been wholly addressed. De la Rosa Blanco and Hileman [8] published a system level noise assessment of the Aurora Flight Sciences/MIT D8 design using correlations that were self-programmed based on documentation of the NASA Aircraft NOise Prediction Program (ANOPP).…”

Section: Introductionmentioning

confidence: 99%

Aircraft System Noise Assessment of the NASA D8 Subsonic Transport Concept

Clark

Thomas

Guo³

2018

2018 AIAA/CEAS Aeroacoustics Conference

View full text Add to dashboard Cite

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.

show abstract

Computational Assessment of the Boundary Layer Ingesting Nacelle Design of the D8 Aircraft

Cited by 45 publications

References 10 publications

Exploring Vehicle Level Benefits of Revolutionary Technology Progress via Aircraft Design and Optimization

Exploring Vehicle Level Benefits of Revolutionary Technology Progress via Aircraft Design and Optimization

Computational Investigation of a Boundary Layer Ingestion Propulsion System for the Common Research Model

Aircraft System Noise Assessment of the NASA D8 Subsonic Transport Concept

Contact Info

Product

Resources

About