![]() Suction will be applied at the leading edge of airframe components such as on the wing, tails or nacelles. “Drag reduction by using laminar flow technology offers a potential double-digit decrease of specific fuel burn for large and faster long range aircraft. So what we’re trying to achieve with our HLFC system is to make sure we maintain the laminarity on the airfoil of the wing and/or the vertical/ horizontal tail plane for as long as possible, so that the air is flowing in parallel layers“. What we’re aiming for is to have the air flow around the airfoil (it can be a wing and/or a vertical/horizontal tailplane) more like the stable, lower part of the flame. There we want to reduce the turbulent part of the flow that is generating drag, which means more fuel consumption. If we transpose this comparison onto an aircraft the air around the wing behaves like the flame. “Think of laminarity as that lower, more stable part of the flame and contrast that with the top part of the flame which is “turbulent“, moving everywhere. The bottom part of the flame is quite stable, but the top of the flame moves erratically“ explains Xavier Hue - Clean Sky 2 Technical Leader at Airbus. Hybrid Laminar Flow Control, the subject of the HLFC Demonstrator project within Clean Sky 2’s Large Passenger Aircraft (LPA) Innovative Aircraft Demonstration Platforms (IADP), is a means to ensure that the air flows around certain parts of the aircraft in parallel layers using a hybrid structure which can be mounted on the leading edge of the tail and of the wing, and by so doing, significant fuel savings and environmental benefits are possible. Dissertation, TU Braunschweig (2018).Laminar flow is the Holy Grail for aerodynamicists, and in fluid dynamics laminar flow occurs when a fluid flows in parallel layers, with no disruption between the layers. 2748 (2020)įehrs, M.: Boundary layer transition in external aerodynamics and dynamic aeroelastic stability. Streit, T.S., Seitz, A., Hein, S., Kunze, P.: NLF potential of laminar transonic long range aircraft. To be Published in New Results in Numerical and Experimental Fluid Mechanics XIII, STAB 2020. ![]() Krimmelbein, N., Krumbein, A.: Determination of critical N-factors for the CRM-NLF wing. Watkins, N., Goodman, K.Z., Peak, S.: Transition detection at cryogenic temperatures using a carbon-based resistive heating layer coupled with temperature sensitive paint. In: 48th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, p. Conical Boundary Layers with Suction, ZARM Technical report (1998)Ĭrouch, J., Sutanto, M., Witkowski, D., Watkins, A., Rivers, M., Campbell, R.: Assessment of the national transonic facility for natural laminar flow testing. Schrauf, G.: COCO - a program to compute velocity and temperature profiles for local and nonlocal stability analysis of compressible. General information CRM-NLF wind tunnel test. Schrauf, G.: LILO 2.1 user’s guide and tutorial. Krumbein, A., Krimmelbein, N., Schrauf, G.: Automatic transition prediction in hybrid flow solver, part 1: methodology and sensitivities. Menter, F.R.: Two-equation eddy-viscosity turbulence models for engineering applications. Model information on and data from the CRM-NLF wind tunnel test. In: 17th International Forum on Aeroelasticity and Structural Dynamics, IFASD, Como (2017) Tichy, L.: Risk analysis for flutter of laminar wings. Seitz, A., Hübner, A., Risse, K.: The DLR TuLam project: design of a short and medium range transport aircraft with forward swept NLF wing. Lynde, M.N., Campbell, R.L., Viken, S.A.: Additional findings from the common research model natural laminar flow wind tunnel test. Lynde, M.N., et al.: Preliminary results from an experimental assessment of a natural laminar flow design method. In: 34th AIAA Applied Aerodynamics Conference, Washington, D.C. 3058 (2017)Ĭampbell, R.L., Lynde, M.N.: Natural laminar flow design for wings with moderate sweep. In: 35th AIAA Applied Aerodynamics Conference, AIAA 2017, Denver, p. Lynde, M.N., Campbell, R.: Computational design and analysis of a transonic natural laminar flow wing for a wind tunnel model.
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