Summary
The contribution of Dasa Airbus to the EUROSHOCK II project in Task 2 and 4 is focused on the assessment of different control devices—active control by cavity/ perforated plate arrangement, discrete suction, and bump— for the application to a hybrid laminar flow wing of a long-range transport aircraft.
The DA viscous inviscid interaction airfoil/swept wing code was improved and extented to treat various shock and boundary layer control devices within Task 2. Extensive computations were carried out for the laminar-type airfoil DRA 2303, the turbulent-type airfoils RAE 5225, MBB Va2 and ADIF and the sheared wing ADIF. The effect of flow control on the pressure distribution could be predicted with sufficient accuracy rendering the code suitable for the application in Task 4 for the control device assessment.
Shock control by using an adaptive bump has shown the greatest potential for drag reduction in the computations as well as in the experiments, while drag reduction by discrete slot suction although successful, is considerably reduced when pump drag is taken into account.
Based on the characteristic features of a laminar wing, the adaptive variable-height bump device seems to be the best means for drag reduction when shock waves are present. A bump parametric study was carried out leading to the establishment of limiting bump parameters and their sensitivity.
For a representative A340-type hybrid laminar flow wing section an adaptive bump design was performed. Its integration into the wing spoiler requires modifications of the A340 wing structure: modification of the wing box, enlargement of the spoiler and introduction of a variable camber flap system for roll control. Two structure and system concepts were suggested for a preliminary realization of the bump integration into the spoiler. Using the wing section polars with the adaptive bump drag characteristics, the estimated drag balance indicates a drag reduction of up to 4% for the complete aircraft and fuel savings of up to 2.1% for a typical transatlantic mission.
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Dargel, G., Thiede, P. (2002). Assessment of Shock and Boundary Layer Control Concepts for Hybrid Laminar Flow Wing Design. In: Stanewsky, E., Délery, J., Fulker, J., de Matteis, P. (eds) Drag Reduction by Shock and Boundary Layer Control. Notes on Numerical Fluid Mechanics and Multidisciplinary Design (NNFM), vol 80. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-540-45856-2_13
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DOI: https://doi.org/10.1007/978-3-540-45856-2_13
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