Abstract
An engineering demonstrator of the winglet active trailing edge (WATE) concept was manufactured by AS03 partners in SARISTU. In parallel, simulation activities were used to investigate the performance benefits of active winglets. A study made by AS03 partners (led by AGI-G) assessed the capacity of the WATE—with a suitably designed controller—to alleviate loads due to gust encounters, and this was used to estimate a structural mass saving of around 2 %. A separate study (performed by AGI-UK and ONERA) investigated the potential for an improvement of the lift-to-drag ratio for off-design conditions. This paper brings together the benefits of the structural mass reduction, and the lift-to-drag improvement, using a form of the well-known Breguet range equation to make estimates of the fuel that can be saved over a given mission. This has been combined with typical fleet operation statistics to estimate that the WATE concept (including the structural mass saving effects) could deliver a 1 % reduction in daily fuel costs for a representative airline fleet. For much of the analysis, simplifying assumptions and models have been used in order to meet the project time and cost objectives. Uncertainty in the precise level of benefit is a risk associated with further development of the WATE technology, but the activities in SARISTU AS03 have demonstrated the potential which makes the WATE concept interesting for further development.
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Abbreviations
- R :
-
Range (or distance between start S1 and start S2 of mission segment)
- V :
-
True airspeed
- f :
-
Specific fuel consumption
- C L /C D :
-
Ratio of the lift coefficient to the drag coefficient (lift-to-drag ratio)
- g :
-
Gravitational acceleration
- W 1 :
-
Weight (mass) at the start of mission segment
- W 2 :
-
Weight (mass) at the end of mission segment
- C Di :
-
Induced drag coefficient
- C D0 :
-
Parasitic drag coefficient
- C Dw :
-
Wave drag coefficient
- AS03:
-
Application scenario 3
- WATE:
-
Winglet active trailing edge
- RANS-CFD:
-
Reynolds averaged Navier–Stokes computational fluid dynamics
- CFD-CSM:
-
CFD coupled to a structural model (for flexible simulations)
- MTOW:
-
Maximum takeoff weight
References
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Acknowledgement
The SARISTU project has received funding from the European Union’s Seventh Framework Programme for research, technological development, and demonstration under Grant Agreement No. 284562.
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Associated SARISTU Documents
Associated SARISTU Documents
Short name | SARISTU PRODAXS location | File |
|---|---|---|
D33.2C | 00-DOCUMENTS/03-AS/Documents/Deliverables | A_DEU_D33_2C_WATE_LoadsAlleviation_R2.pdf |
D33.2E | 00-DOCUMENTS/03-AS/Documents/Deliverables | A_DEU_D33_2E_WATE_DragAssessment_R1.pdf |
D33.2F | 00-DOCUMENTS/03-AS/Documents/Deliverables | A_DEU_D33_2F_WATE_FuelBurn_R01_sign_rep.pdf |
D12.1.1 | 00-DOCUMENTS/12-IS/Documents/Deliverables | SARISTU 12.1.1 Iss_1.pdf—reference baseline wing and morphing wing aeromechanical requirements |
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© 2016 Springer International Publishing Switzerland
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Herring, M. (2016). Evaluation of the Performance Benefits of the Winglet Active Trailing Edge in AS03. In: Wölcken, P., Papadopoulos, M. (eds) Smart Intelligent Aircraft Structures (SARISTU). Springer, Cham. https://doi.org/10.1007/978-3-319-22413-8_17
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DOI: https://doi.org/10.1007/978-3-319-22413-8_17
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Online ISBN: 978-3-319-22413-8
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