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Wednesday, April 22, 2020 | History

3 edition of The natural flow wing-design concept found in the catalog.

The natural flow wing-design concept

The natural flow wing-design concept

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  • 40 Currently reading

Published by National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, For sale by the National Technical Information Service] in [Washington, DC], [Springfield, Va .
Written in English

    Subjects:
  • Airplanes -- Wings, Triangular -- Design and construction.,
  • Aerodynamics, Supersonic.,
  • Drag (Aerodynamics)

  • Edition Notes

    StatementRichard M. Wood and Steven X.S. Bauer.
    SeriesNASA technical paper -- 3193.
    ContributionsUnited States. National Aeronautics and Space Administration. Scientific and Technical Information Program.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL18053639M

    The new blended-wing body, or "flying wing," design does away with the cigar-shaped fuselage and tail section that have been mainstays of modern passenger planes since they took off in the s. The flying-wing design fuses together the wings and fuselage into one sleek vehicle that resembles a : Kevin Bonsor. FACTORS AFFECTING MASS AND BALANCE IN AIRCRAFT • THE EFFECT OF CG LOCATION VS. CP LOCATION: When the CG is forward of the CP, there is a natural tendency for the aircraft to want to pitch nose down. If the CP is forward of the CG, a nose up pitching moment is created. This increases AoA, causing the CP to move further forward and can lead. account T.S.I. and C.F.I. The Natural Laminar Flow (NLF) concept can only be applied to the following configurations: (a) low sweep and moderate Reynolds numbers; (b) high sweep and small Reynolds numbers. For the current high sweep and high Reynolds numbers encountered on large transport aircraft, it is necessary to maintain laminar flow by.


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The natural flow wing-design concept Download PDF EPUB FB2

Get this from a library. The natural flow wing-design concept. [Richard M Wood; United States. National Aeronautics and Space Administration. Scientific and Technical Information Program.]. The Natural Flow Wing-Design Concept Richard M.

Wood and Steven X. Bauer Langley Research Center Hampton, Virginia. Nomenclature A cross-sectional area, in 2 ai variables used to define airfoil geom-etry forward of maximum thickness (where i = 0, 1, 2, or 3) b wing span, in. natural laminar flow wing design concept by using previous design system and verified the effect of its design concept by the flight test of Japan Aerospace Exploration Agency in The overall design system consists of the flow solver, a design module based on an inverse design problem and its interface module.

runs of natural laminar flow, static pressure thrust, and a wake filling effect for a design Mach of A series of experiments were conducted on cross-flow fans in transonic flow conditions in order to evaluate their suitability for the suction system requirements of this Size: 7MB.

that economic hurdle. Natural laminar flow (NLF) wing design technology is an important means to reduce the aerodynamic drag. The. Japan Aerospace Exploration Agency (JAXA) developed a scaled supersonic experimental airplane called -1 in National NEXST EXperimental Supersonic Transport (NEXST) project with the NLF wing design concept andFile Size: KB.

designed to obtain significant amounts of natural laminar flow (NLF) (refs. 4, 5, and 6). Two recent NLF research results should be considered in developing new lifting surface designs: (I) the feasibility of maintaining NLF at large values of transition Reynolds number, and (2) the ability to.

Richard M. Wood has written: 'The natural flow wing-design concept' -- subject(s): Aerodynamics, Supersonic, Airplanes, Design and construction, Drag (Aerodynamics), Supersonic Aerodynamics.

The concept of using shock control bump is to control supersonic flow on the suction/pressure side of natural laminar flow aerofoil that leads to delaying shock. An airfoil (American English) or aerofoil (British English) is the cross-sectional shape of a wing, blade (of a propeller, rotor, or turbine), or sail (as seen in cross-section).

An airfoil-shaped body moving through a fluid produces an aerodynamic component of this force perpendicular to the direction of motion is called component parallel to the direction of motion is.

The Reno, Nev., firm working to shatter business jet speed records by going supersonic announced Feb. 14 that flight testing has begun on a refined wing design.

NASA’s Dryden Flight Research Center has attached a scaled-down section of the supersonic natural laminar flow wing to the belly of an FB for flights to Mach A natural flow wing design employing 3-D nonlinear analysis applied at supersonic speeds.

A new airfoil design concept. A direct-inverse transonic wing-design method in curvilinear coordinates including viscous-interaction. ROBERT RATCLIFF and. Wing Design 4 One of the necessary tools in the wing design process is an aerodynamic technique to calculate wing lift, wing drag, and wing pitching moment.

With the progress of the science of aerodynamics, there are variety of techniques and. This is the first attempt to apply the natural laminar flow wing concept to a supersonic vehicle. The concept of the natural laminar flow wing is validated by measuring the surface pressure and.

Although the overall appearance of modern airliners has not changed a lot since the introduction of jetliners in the s, their safety, efficiency and environmental friendliness have improved considerably. Main contributors to this have been gas turbine engine technology, advanced materials, computational aerodynamics, advanced structural analysis and on-board Author: Egbert Torenbeek.

airfoil here was designed for an ultralight sailplane requiring very high maximum lift coefficients with small pitching moments at high speed. One possible solution: a variable geometry airfoil with flexible lower surface.

The airfoil used on the Solar Challenger, an aircraft that flew across the English Channel on solar power,File Size: KB. General NASA must continue to provide the necessary resources for aerodynamics research and validation, including resources focused on specific key technologies, resources to maintain and enhance ground and flight test facilities, and resources for enhanced analytical and design capabilities.

Specific. The following research topics should serve as the focus of NASA's. The book dives from general concept to detailed analysis and back to general concept pretty much at-will.

It looks and reads more like a large collection of lecture notes and chalkboard analysis, with an occasional personal philosophy thrown in/5(27). Neutral Point and Stability. As we learned above, an unswept wing with a reflexed airfoil is able to stabilize itself. Its c.g. must be located in front of the c/4 point, which is also called neutral point (n.p.).The distance between the neutral point (quarter chord point for an unswept wing) and the center of gravity is defining the amount of stability - if the c.g.

is close to the n.p., the. implementation of hybrid or natural laminar flow concepts.” It is especially the second statement what we currently target in our design work on Krüger devices to enable laminar wing technology.

Krueger design for a natural laminar flow (NLF) wing. In the frame of the project “Design, Simulation and Flight Reynolds Number TestingFile Size: KB. Aerodynamics, from Greek ἀήρ aero (air) + δυναμική (dynamics), is the study of motion of air, particularly as interaction with a solid object, such as an airplane wing.

It is a sub-field of fluid dynamics and gas dynamics, and many aspects of aerodynamics theory are common to these term aerodynamics is often used synonymously with gas dynamics, the difference.

Wing Design Figure Wing design procedure Identify and prioritize wing design requirements (Performance, stability, producibility, operational requirements, cost, flight safety) Select wing vertical location Select or design wing airfoil. • Flying at same speed, all-wing design can fly % farther •The N-1M proved the feasibility of the flying wing concept and was used to refine the overall design •The N-1M was controlled by elevons and drag rudders on the wing tips •Hidden in the airfoil, the original N-1M engines suffered from over-heating File Size: 3MB.

Theory of Wing Sections: Including a Summary of Airfoil Data (Dover Books on Aeronautical Engineering) - Kindle edition by Abbott, Ira H., Doenhoff, A. von. Download it once and read it on your Kindle device, PC, phones or tablets.

Use features like bookmarks, note taking and highlighting while reading Theory of Wing Sections: Including a Summary of Airfoil Data /5(90). Inverse method for NLF (Natural Laminar Flow) wing design A lot of wind tunnel tests and CFD analysis for NEXST configurations were conducted to predict its performance, before the flight tests.

In the 3rd SST-workshop held in Dec. many researchers supplied the CFD analysis results of NEXST-1 calculated with their own : Shinkyu Jeong, Ryo Takaki, Kazuomi Yamamoto. The true potential of the concept was not yet demonstrated in flight. Perhaps some day it will be demonstrated and a mission capable X-Wing will enter service.

With the X-Wing program Sikorsky gained much technical experience on bearingless composite rotors, and fly-by-wire and higher harmonic control systems, which greatly advanced these.

The aerodynamic constraints include a lift coefficient ofa pitching moment coefficient greater than − and wave drag coefficent less than The flow condition is at a free stream Mach number ofan angle of attack at 0 deg., and a Reynolds number of × 10 7.

The Navier-Stokes equations are solved using C type of mesh. MEC Fluid Mechanics. CHE Fluid Mechanics Lecturer Kenny Tan Boon Thong Room @ Office: (Internal) or H/P: Common Activity Lectures Monday 10am in Audi 1 Tuesday 2pm in Audi 1 Wednesday 9am in Audi 1 Tutorials Wednesday pm in Audi 1 Labs/ Practice Class Monday 3pm, Thursday.

recent developments of the FanWing concept could now uniquely offer short-field performance close to that of helicopters and tilt-rotor aircraft, but with operating economies close to that of conventional aircraft.

Introduction This paper briefly reviews the history of the FanWing aircraft concept and then reportsFile Size: KB. Summer Science For the Royal Society's Summer Science ExhibitionImperial College London, Institut de Méchanique de Fluides de Toulouse (IMFT) and Laboratoire PLAsma et Conversion d'Energie (LAPLACE) have come together to.

The current numerical solver for the flow field around an unsteady rotating airfoil was validated against the published numerical data. It was confirmed that the corrugated airfoil performs (in terms of the lift-to-drag ratio) much better than the profiled NACA airfoil at low Reynolds number R e = in low angle of attack range of 0.

That's percent the full size aircraft, but big enough to prove the concept. Dye in the water, moving at 10 inches per second, charts how the airflow moves across the airplane's surface, called Author: Joe Pappalardo.

The key to Aerion’s design is a concept called natural laminar flow proposed by aerodynamicist and Aerion founder Richard Tracy, who has had a hand in such diverse and innovative aircraft as the Canadair Challenger business and the single-stage-to-orbit Rockwell X spaceplane concept.

Northrop Grumman reached deep into its history, as well as its recent past, to draw inspiration for an airliner of the future — a flying wing much like the B-2 stealth bomber.

The firm designed. Optimal design of natural and hybrid laminar flow control on wings. Jan Pralits Department of Mechanics, Royal Institute of Technology SE 44 Stockholm, Sweden.

Abstract Methods for optimal design of different means of control are developed in this thesis. The main purpose is to maintain the laminar flow on wings at a chord.

a turbulent flow. • Turbulent boundary layer—dominated by eddies and irregular turbulent flow. [Figure ] Turbulent boundary layers generate 5 to 10 times more skin friction drag than the equivalent laminar boundary layer.

[Figure ] Therefore, glider designers try to maintain laminar flow across as much of the aircraft as possible. Natural Laminar Flow Laminar Flow Control Hybrid Laminar Flow Control Gains, Challenges and Barriers of LFC Induced Drag Reduction Wing Span Spanwise Camber Non-planar Wing Systems Bibliography 5 From Tube and Wing to Flying Wing The Case for Flying Wings File Size: 4MB.

Anderson's book is a good text for understanding the building blocks of fluid dynamics, such as the different types of flow. It is good for understanding how airfoils and wings work, as well as understanding the microscopic flow considerations.

The History of Laminar Flow The North American P Mustang was the first aircraft intentionally designed to use laminar flow airfoils.

However, wartime National Advisory Committee for Aeronautics (NACA) research data shows that Mustangs were not manufactured with a sufficient degree of surface quality to maintain much laminar flow on the wing.

HALE UAVs developed in the past 30 years represent a wide range of flow conditions. From the low-speed Predator (Ernst, ) and Condor (Johnstone and Arntz, ) to Global Hawk (Heber, ) and Darkstar (Berman, ), these aircraft share several aerodynamic challenges, but also illustrate the differences among UAVs in this class.

M referred to undisturbed flow conditions. M* equivalent Mach number characterizing the extent of supercritical flow in the design condition. N e. number of engines. load factor = L/W. P to. total static (equivalent) engine power of all engines at sea level.

ambient pressure. P o. p at sea level. p ∞ p of undisturbed flow. dynamic Cited by: 1. The technical books below have proven useful during years of aircraft conceptual design experience in industry and during the writing of AIRCRAFT DESIGN: A Conceptual Approach, the RDS design software, and Dan Raymer's Simplified Aircraft Design for Homebuilders.I actually own almost every one of them and use them often.•The flow follows the contours of the skin •Lift varies linearly with angle of attack •At high angle of attack, flow over the upper surface separates.

•Flow no longer follows the upper-surface skin •This causes a loss of upper-surface lift •When the separated region gets File Size: 1MB.Flapping-wing Micro Air Vehicles (FW-MAVs), inspired by small insects, have limitless potential to be capable of performing tasks in urban and indoor environments.

Through the process of mimicking insect flight, however, there are a lot of challenges for successful flight of these vehicles, which include their design, fabrication, control, and : Boon Hong Cheaw, Hann Woei Ho, Elmi Abu Bakar.