| Autor: |
Tanguy, Geoffrey, Monnier, Jean Claude, Verbeke, Christophe, Wild, Jochen |
| Jazyk: |
angličtina |
| Rok vydání: |
2022 |
| Předmět: |
|
| Zdroj: |
9ᵀᴴ EUROPEAN CONFERENCE FOR AERONAUTICS AND SPACE SCIENCES (EUCASS) |
| Popis: |
Future aircraft design may require the use of laminar wing in order achieve the targets for emission reduction set by the ACARE Vision 2020 and FlightPath 2050 strategies for future air transport. The integration of high lift system for laminar wing remains one of the main challenges in the field. Classical high lift configuration using slat devices are proscribed with laminar wing due to the introduction of turbulence into the flow over the upper side of the wing. In addition, there is a need to shield the leading edge of the wing during low altitude flight where pollution and insect could adversely impact the laminarity of the main wing for cruise conditions [1]. The Unsteady High-lift Aerodynamics Unsteady RANS Validation project (UHURA) investigates a Krueger flap leading edge devices both experimentally and numerically. The Krueger is represented by an additional lift surface concept that is deployed during the flight from the lower side of the wing for take-off and landing [2]. The concept of the Krueger was initiated in the 1940s [3] and was first found to be promising high-lift system for laminar wing technology during the NASA B757 laminar wing flight test program [4]. However, due to its complexity and the potential development of critical unsteadiness within the flow during the deployment, the classical slat device was preferred by aircraft manufacturer [1] and was highly investigated in the literature [5, 6]. Today, the Krueger devices capability to shield the leading edge of the wing during take and its promising performances makes it a suitable candidate for laminar wing device. Within the UHURA project, a recent wind tunnel test campaign was conducted at the ONERA L1 wind tunnel [7] using the DLR-F15 [8] Airfoil model that features a full span Krueger device, which can be actuated at high deflection rates up to 180/s. The tests include the measurements steady and unsteady static pressure as well as phase-locked Particle Image Velocimetry (PIV) on the lower section of the wing. The high spatial resolution synchronous measurement permits a detailed assessment of the flow velocity and unsteadiness to provide a first step in understanding the dynamic flow field during the Krueger deployment and retraction phases. The high number of static pressure measurements will allow to calculate the variation of aerodynamic forces over the Krueger during multiple cycles. The impact of the deployment speed and flow velocity will also be investigated. |
| Databáze: |
OpenAIRE |
| Externí odkaz: |
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