Hybrid Wing Body Performance Validation at the National Transonic Facility

Wick, Andrew; Hooker, John R.; Walker, Jimmy; Chan, David T.; Plumley, Ryan W.; Zeune, Cale

doi:10.2514/6.2017-0099

Cited by 9 publications

(6 citation statements)

References 9 publications

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“…The vertical stabilizer went through several design iterations to minimize interference with the tunnel sidewall because CFD simulations showed that keeping the inboard half of the vertical stabilizer created a convergent/divergent nozzle effect with the sidewall and led to shockinduced flow separation at the trailing edge. 10 The final design, as shown in Figure 12, included a flat surface on the inboard side to minimize the interference with the sidewall but retained the upper bullet shape in order to have enough material to mount the horizontal tail. A nonmetric standoff is used to offset the model from the tunnel sidewall and the metric break is preserved through the use of a labyrinth seal.…”

Section: Methodsmentioning

confidence: 99%

Transonic Semispan Aerodynamic Testing of the Hybrid Wing Body with Over Wing Nacelles in the National Transonic Facility

Chan

Hooker

Wick

et al. 2017

55th AIAA Aerospace Sciences Meeting

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A wind tunnel investigation of a 0.04-scale model of the Lockheed Martin Hybrid Wing Body (HWB) with Over Wing Nacelles (OWN) air mobility transport configuration was conducted in the National Transonic Facility at the NASA Langley Research Center under a collaborative partnership between NASA, the Air Force Research Laboratory, and Lockheed Martin Aeronautics Company. The wind tunnel test sought to validate the transonic aerodynamic performance of the HWB and to validate the efficiency benefits of the OWN installation as compared to the traditional under-wing installation. The semispan HWB model was tested in a clean wing configuration and also tested with two different nacelles representative of a modern turbofan engine and a future advanced high bypass ratio engine. The nacelles were installed in three different locations with two over-wing positions and one under-wing position. Five-component force and moment data, surface static pressure data, and aeroelastic deformation data were acquired. For the cruise configuration, the model was tested in an angle-of-attack range between -2 and 10 degrees at free-stream Mach numbers from 0.3 to 0.9 and at unit Reynolds numbers between 8 and 39 million per foot, achieving a maximum of 80% of flight Reynolds numbers across the Mach number range. The test results validated pretest computational fluid dynamic (CFD) simulations of the HWB performance including the OWN benefit and the results also exhibited excellent transonic drag data repeatability to within ±1 drag count. This paper details the experimental setup and model overview, presents some sample data results, and describes the facility improvements that led to the success of the test.

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Section: Methodsmentioning

confidence: 99%

Transonic Semispan Aerodynamic Testing of the Hybrid Wing Body with Over Wing Nacelles in the National Transonic Facility

Chan

Hooker

Wick

et al. 2017

55th AIAA Aerospace Sciences Meeting

Self Cite

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“…14 The positioning of the engines was motivated by the potential of additional 4% increase of aerodynamic efficiency with potentially minor weight penalties due to installation. 14,73,74 The allocation of the fuel tanks is shown in Figure 5 where two integral tanks are located in front and behind the cabin. This configuration showed the most stable allocation of the aircraft center of gravity compared to the configuration which had both tanks located behind the cabin.…”

Section: Lh2 Aircraft Designmentioning

confidence: 99%

Comparative study of hydrogen and kerosene commercial aircraft with advanced airframe and propulsion technologies for more sustainable aviation

Karpuk

Elham

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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Present work performs a comparative study of two medium-range commercial jets with future airframe and propulsion technologies powered by hydrogen and kerosene fuel to achieve a substantial reduction in overall aviation emissions. The study aims to investigate the cumulative effect of different energy networks combined with airframe efficiency gains achieved by aircraft-related technologies to suggest a better option for the potential next-generation commercial aircraft similar to the Airbus A320. Advanced airframe and engine technologies include laminar flow control, active load alleviation, new materials and structures, and ultra-high bypass ratio turbofan engines. Two aircraft with hydrogen and kerosene propulsion systems were sized to compare their performance characteristics, equivalent CO2 emission, and direct operating costs. The design was performed using a multi-fidelity approach and included the effects of future airframe technologies and the hydrogen propulsion system. The design comparison showed a significant contribution of airframe and propulsion technologies in achieving more environmentally friendly aircraft. The green hydrogen option showed a 41–63% reduction in overall emissions compared to the kerosene aircraft depending on flight conditions while the blue hydrogen variant achieved a 21–26% reduction level. A rather optimistic price scenario shall be met to enable an operational benefit of green hydrogen while the blue hydrogen variant has more potential of being economically acceptable by the market. In circumstances when operating costs drive the decision-making more than emissions, kerosene may be a more favorable option as a compromise between emission and costs, given the positive effect of airframe and propulsion technologies.

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“…The LM-HWB configuration uses the same leading edge slats and Fowler flaps as conventional aircraft [8]. This conventional lift enhancement method requires complex working mechanisms for safe operation, usually covered by fairings and protruding under the wings, creating detrimental drag [9].…”

Section: Introductionmentioning

confidence: 99%

Experimental Investigation on the Combined Blowing Control of a Hybrid Wing Body Aircraft

et al. 2023

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Combined blowing was performed on a Hybrid Wing Body (HWB) aircraft through wind tunnel testing at a Reynolds number of 1.75 × 106. The full cycle of separation and reattachment under the control of combined blowing was implemented using Computational Fluid Dynamics (CFD), and the mechanism of combined blowing inhibiting separation was analyzed. The aerodynamic characteristics of the baseline and the independent effects of the blown deflected trailing edge (TE), blown leading edge (LE), and combined blowing on the TE and LE were investigated. The results clearly show that combined blowing can inhibit the development of cross-flow, reduce the accumulation of a boundary layer at the tip, and inhibit the flow separation effect. The effect of using seamless simple flaps alone to increase the lift is limited; blowing control is required to enhance the lift further. Applying the blown deflected TE can improve the lift linear segment, so that 30° flap achieves the lift gain of 40° flap without control, while the drag coefficient is approximately 0.02 smaller, but the stall gradually advances. Using the blown LE can significantly increase the stall angle from 12° to 18°. However, the lift linear segment remains unaffected. In particular, combined blowing can achieve the control effect of improving the lift linear segment, delaying stall, and decreasing drag. Moreover, the maximum lift coefficient is approximately 0.19, and the lift-to-drag ratio increment in the control state with a 30° flap deflection angle is above 2.2 in the angle of attack range of 4° to 12° compared to the uncontrolled state with a 40° flap deflection angle.

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Hybrid Wing Body Performance Validation at the National Transonic Facility

Cited by 9 publications

References 9 publications

Transonic Semispan Aerodynamic Testing of the Hybrid Wing Body with Over Wing Nacelles in the National Transonic Facility

Transonic Semispan Aerodynamic Testing of the Hybrid Wing Body with Over Wing Nacelles in the National Transonic Facility

Comparative study of hydrogen and kerosene commercial aircraft with advanced airframe and propulsion technologies for more sustainable aviation

Experimental Investigation on the Combined Blowing Control of a Hybrid Wing Body Aircraft

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