Search results for: overview-of-laminar-flow-control

Overview of Laminar Flow Control

Author : Ronald D. Joslin
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Natural Laminar Flow and Laminar Flow Control

Author : R.W. Barnwell
File Size : 76.81 MB
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Research on laminar flow and its transition to turbulent flow has been an important part of fluid dynamics research during the last sixty years. Since transition impacts, in some way, every aspect of aircraft performance, this emphasis is not only understandable but should continue well into the future. The delay of transition through the use of a favorable pressure gradient by proper body shaping (natural laminar flow) or the use of a small amount of suction (laminar flow control) was recognized even in the early 1930s and rapidly became the foundation of much of the laminar flow research in the U.S. and abroad. As one would expect, there have been many approaches, both theoretical and experimental, employed to achieve the substantial progress made to date. Boundary layer stability theories have been formu lated and calibrated by a good deal of wind tunnel and flight experiments. New laminar now airfoils and wings have been designed and many have been employed in aircraft designs. While the early research was, of necessity, concerned with the design of subsonic aircraft interest has steadily moved to higher speeds including those appropriate to planetary entry. Clearly, there have been substantial advances in our understanding of transition physics and in the development and application of transition prediction methodolo gies to the design of aircraft.

Overview of Supersonic Laminar Flow Control Research on the F 16XL Ships 1 and 2

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The NASA Langley Laminar flow control Experiment on a Swept Supercritical Airfoil Evaluation of Initial Perforated Configuration

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An Overview of Recent Subsonic Laminar Flow Control Flight Experiments

Author : F. S. Collier
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Summary of Laminar Flow Control Techniques for Aircraft

Author : Philip P. Antonatos
File Size : 74.32 MB
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Survey and Bibliography on Attainment of Laminar Flow Control in Air Using Pressure Gradient and Suction Volume 1

Author : Dennis M. Bushnell
File Size : 59.38 MB
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NASA F 16xl Supersonic Laminar Flow Control Program Overview

Author : National Aeronautics and Space Adm Nasa
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The viewgraphs and discussion of the NASA supersonic laminar flow control program are provided. Successful application of laminar flow control to a High Speed Civil Transport (HSCT) offers significant benefits in reductions of take-off gross weight, mission fuel burn, cruise drag, structural temperatures, engine size, emissions, and sonic boom. The ultimate economic success of the proposed HSCT may depend on the successful adaption of laminar flow control, which offers the single most significant potential improvements in lift drag ratio (L/D) of all the aerodynamic technologies under consideration. The F-16XL Supersonic Laminar Flow Control (SLFC) Experiment was conceived based on the encouraging results of in-house and NASA supported industry studies to determine if laminar flow control is feasible for the HSCT. The primary objective is to achieve extensive laminar flow (50-60 percent chord) on a highly swept supersonic wing. Data obtained from the flight test will be used to validate existing Euler and Navier Stokes aerodynamic codes and transition prediction boundary layer stability codes. These validated codes and developed design methodology will be delivered to industry for their use in designing supersonic laminar flow control wings. Results from this experiment will establish preliminary suction system design criteria enabling industry to better size the suction system and develop improved estimates of system weight, fuel volume loss due to wing ducting, turbocompressor power requirements, etc. so that benefits and penalties can be more accurately assessed. Fischer, Michael C. Langley Research Center ...

The NASA Langley Laminar Flow Control Lfc Experiment on a Swept Supercritical Airfoil

Author : National Aeronautics and Space Administration (NASA)
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A large-chord, swept, supercritical, laminar-flow-control (LFC) airfoil was designed and constructed and is currently undergoing tests in the Langley 8 ft Transonic Pressure Tunnel. The experiment was directed toward evaluating the compatibility of LFC and supercritical airfoils, validating prediction techniques, and generating a data base for future transport airfoil design as part of NASA's ongoing research program to significantly reduce drag and increase aircraft efficiency. Unique features of the airfoil included a high design Mach number with shock free flow and boundary layer control by suction. Special requirements for the experiment included modifications to the wind tunnel to achieve the necessary flow quality and contouring of the test section walls to simulate free air flow about a swept model at transonic speeds. Design of the airfoil with a slotted suction surface, the suction system, and modifications to the tunnel to meet test requirements are discussed. Harris, Charles D. and Harvey, William D. and Brooks, Cuyler W., Jr. Langley Research Center BOUNDARY LAYER CONTROL; LAMINAR BOUNDARY LAYER; LAMINAR FLOW; SUPERCRITICAL AIRFOILS; SWEPT WINGS; AIRCRAFT DESIGN; DRAG REDUCTION; FREE FLOW; GENERAL OVERVIEWS; PREDICTION ANALYSIS TECHNIQUES; SUCTION; TRANSONIC SPEED; WIND TUNNEL TESTS; WIND TUNNEL WALLS; WING SLOTS...

Research in Natural Laminar Flow and Laminar Flow Control Part 3

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A History of Suction type Laminar flow Control with Empahsis i e Emphasis on Flight Research

Author : Albert L. Braslow
File Size : 45.69 MB
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The NASA Langley Laminar flow control Experiment on a Swept Supercritical Airfoil

Author : Charles D. Harris
File Size : 32.43 MB
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Research in Natural Laminar Flow and Laminar Flow Control Part 1

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File Size : 57.5 MB
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A Flight Test of Laminar Flow Control Leading edge Systems

Author : M. C. Fischer
File Size : 80.58 MB
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Natural Laminar Flow and Laminar Flow Control

Author : R.W. Barnwell
File Size : 80.49 MB
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Research on laminar flow and its transition to turbulent flow has been an important part of fluid dynamics research during the last sixty years. Since transition impacts, in some way, every aspect of aircraft performance, this emphasis is not only understandable but should continue well into the future. The delay of transition through the use of a favorable pressure gradient by proper body shaping (natural laminar flow) or the use of a small amount of suction (laminar flow control) was recognized even in the early 1930s and rapidly became the foundation of much of the laminar flow research in the U.S. and abroad. As one would expect, there have been many approaches, both theoretical and experimental, employed to achieve the substantial progress made to date. Boundary layer stability theories have been formu lated and calibrated by a good deal of wind tunnel and flight experiments. New laminar now airfoils and wings have been designed and many have been employed in aircraft designs. While the early research was, of necessity, concerned with the design of subsonic aircraft interest has steadily moved to higher speeds including those appropriate to planetary entry. Clearly, there have been substantial advances in our understanding of transition physics and in the development and application of transition prediction methodolo gies to the design of aircraft.

Laminar Flow Control Technology

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File Size : 65.25 MB
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Research in Natural Laminar Flow and Laminar Flow Control Part 2

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File Size : 72.87 MB
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Survey and Bibliography on Attainment of Laminar Flow Control in Air Using Pressure Gradient and Suction

Author : Dennis M. Bushnell
File Size : 90.51 MB
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Evaluation of Laminar Flow Control Systems for Subsonic Commercial Transport Aircraft Executive Summary

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Evaluation of Laminar Flow Control System Concepts for Subsonic Commercial Transport Aircraft

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