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Experimental Results for a Flapped Natural-laminar-flow Airfoil with High Lift/drag Ratio
TLDR
In this article, a flapped natural-laminar flow airfoil, NLF(1)-0414F, was designed for 0.70 chord laminar flow on both surfaces at a lift coefficient of 0.40.Abstract:
Experimental results have been obtained for a flapped natural-laminar-flow airfoil, NLF(1)-0414F, in the Langley Low-Turbulence Pressure Tunnel. The tests were conducted over a Mach number range from 0.05 to 0.40 and a chord Reynolds number range from about 3.0 x 10(6) to 22.0 x 10(6). The airfoil was designed for 0.70 chord laminar flow on both surfaces at a lift coefficient of 0.40, a Reynolds number of 10.0 x 10(6), and a Mach number of 0.40. A 0.125 chord simple flap was incorporated in the design to increase the low-drag, lift-coefficient range. Results were also obtained for a 0.20 chord split-flap deflected 60 deg.read more
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Overview of Laminar Flow Control
TL;DR: The history of Laminar Flow Control (LFC) from the 1930s through the 1990s is reviewed and the current status of the technology is assessed in this paper, where early studies related to the natural laminar boundary-layer flow physics, manufacturing tolerances for laminAR flow, and insect-contamination avoidance are discussed.
Ice Accretions and Icing Effects for Modern Airfoils
TL;DR: Icing tests were conducted to document ice shapes formed on three different two-dimensional airfoils and to study the effects of the accreted ice on aerodynamic performance as discussed by the authors, which were representative of airfoil designs in current use for each of the commercial transport, business jet, and general aviation categories of aircraft.
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Gurney Flap Experiments on Airfoil and Wings
Experimental Investigation of Water Droplet Impingement on Airfoils, Finite Wings, and an S-duct Engine Inlet
Michael Papadakis,Kuohsing E. Hung,Giao T. Vu,Hsiung Wei Yeong,Colin S. Bidwell,Martin D. Breer,Timothy J. Bencic +6 more
TL;DR: In this paper, the authors presented improved experimental and data reduction methods for obtaining water droplet impingement data and provided a comprehensive water-droplet impeding database for a range of test geometries including an MS(1)-0317 airfoil, a GLC-305 airfoil, an NACA 65(sub 2)-415 airfool, a commercial transport tail section, a 36-inch chord natural laminar flow NLF (1)-0414 airfoils, a 48-inch NLF(1-0414 section with
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Flow Separation Control with Microflexural Wall Vibrations
TL;DR: In this article, a capacitively actuated active flexible wall (AFW) transducer has been developed for controlling boundary-layer flow separation, where the transducers are first used as sensors to determine the most effective frequencies for wall actuation in the vicinity of a separating or marginally separated boundary layer.