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Tuesday, May 19, 2020 | History

3 edition of Supersonic, nonlinear, attached-flow wing design for high lift with experimental validation found in the catalog.

Supersonic, nonlinear, attached-flow wing design for high lift with experimental validation

Jimmy L. Pittman

Supersonic, nonlinear, attached-flow wing design for high lift with experimental validation

by Jimmy L. Pittman

  • 171 Want to read
  • 14 Currently reading

Published by National Aeronautics and Space Administration, Scientific and Technical Information Branch, For sale by the National Technical Information Service] in [Washington, D.C.], [Springfield, Va .
Written in English

    Subjects:
  • Airplanes -- Wings.,
  • Aerodynamics, Supersonic.

  • Edition Notes

    Other titlesSupersonic, nonlinear, attached flow wing design for high lift with experimental validation.
    StatementJames L. Pittman and David S. Miller, William H. Mason.
    SeriesNASA technical paper -- 2336.
    ContributionsMiller, David S., Mason, William H. 1947-, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.
    The Physical Object
    FormatMicrofiche
    Pagination1 v.
    ID Numbers
    Open LibraryOL14663899M

    Sonic Boom Consideration in Preliminary Design of Supersonic Aircraft 1 INTRODUCTION Since the development in of the first operational supersonic fighter, the F, constant efforts have been undertaken to make routine high-speed flight a reality. A supersonic airfoil is a cross-section geometry designed to generate lift efficiently at supersonic speeds. The need for such a design arises when an aircraft is required to operate consistently in the supersonic flight regime. Supersonic airfoils generally have a thin section formed of either angled planes or opposed arcs (called "double wedge airfoils" and "biconvex airfoils" respectively.

    supersonic biplane at the design and off-design Mach number conditions by supersonic blow-down wind tunnel test facility. Especially, the shock wave patterns and characteristics around supersonic biplane were investigated by Schlieren method. Moreover, the lower wing surface pressure profiles of supersonic biplane. FXL Supersonic Laminar Flow. Laminar flow at supersonic speeds was successfully achieved in a two-phased NASA flight research program that used two delta-wing FXL aircraft from to to investigate active and passive laminar flow control (LFC) as a potential technology for a future High Speed Civil Transport (HSCT).

    Drag coefficient of trimmed wing (~/~. constant) Lift coefficient of trimmed wing (~h. constant) Variation with C,,~ with C L at supersonic speeds; moment reference centre at 0"45~ to give neutral stability at M = , C L = Drag coefficient of trimmed wing, C c = IV. Lift and Drag Characteristics of Delta Wings at Supersonic Speeds Figure 1. Lift Characteristics of Delta Wings 50 2. Form Drag of Delta Airfoils Whose Leading Edges are Inside the Mac'r«. Cone, 50 3. Lift-Drag Eatio of Delta and Rectangular Wings 51 4.» Maximum Lift-Drag Ratio - Delta Wings, 51 5. Maximum Lift-Drag Eatio 51 Size: 1MB.


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Supersonic, nonlinear, attached-flow wing design for high lift with experimental validation by Jimmy L. Pittman Download PDF EPUB FB2

Results of the experimental validation are presented for the three dimensional cambered nonlinear which was designed to achieve attached supercritical cross flow for lifting conditions typical of supersonic maneuver.

The design point was a lift coefficient of at Mach and 12 deg angle of attack. Results from the nonlinear full potential.

Get this from a library. Supersonic, nonlinear, attached-flow wing design for high lift with experimental validation. [Jimmy L Pittman; David S Miller; William H Mason; United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.].

Full text of "Supersonic, nonlinear, attached-flow wing design for high lift with attached-flow wing design for high lift with experimental validation book validation" See other formats. Results of the experimental validation are presented for the three dimensional cambered wing which was designed to achieve attached supercritical cross flow for lifting conditions typical of supersonic maneuver.

The design point was a lift coefficient of at Mach and 12 deg angle of attack. Results from the nonlinear full potential Author: J. Pittman, W. Mason and D. Miller. Division II: Aerodynamics, Volume 7: Wing Theory in Supersonic Flow examines the cases of isolated simple wings, wings with vertical plane tail, cruciform wings, and simple or cruciform wings fitted with a body.

This book presents the method for the actual calculation of isolated wings or. 's and 's, a new concept for supersonic wing design emerged. The SC' wing concept provides a means of achieving attached flow high lift efficiently at supersonic speeds.

The idea was originated in at Grumman by R. Meyer and is illustrated schematically in figure Size: 3MB. Conceptual Design of High Speed Supersonic Aircraft: A brief review on SR (Blackbird) Aircraft Hui Xue1, a) H. Khawaja2, b) and M. Moatamedi3, c) 1Master Student, Faculty of Technology, Narvik University College, Narvik, Norway.

2Associate Professor, Department of Engineering and Safety, University of Tromsø, Tromsø, Norway. 3Professor, Faculty of Technology, Narvik University College. In subsonic flight the wing generates lift by means of accelerating the flow around the top surface of the airfoil, this is achieved by altering the chord, upper & lower camber, curvature and the angle of attack in order to produce an area of lower pressure above the airfoil.

In supersonic flight, lift is generated only by the angle of attack. Nonlinear lift control at high speed and high angle of attack using vortex flow technology. Detailed flowfield measurements over a 75 deg swept delta wing for code validation. January tion of Supersonic Inlet Buzz J Effects of Forced Asymmetric Tran-sition on Vortex Asymmetry Around Slender Bodies J Effective Inflow Conditions for Turbu-lence Models in Aerodynamic Calculations J Lift Enhancement over Flexible Nons-lender Delta Wings J Efficient Approach for Multipoint Aerodynamic Wing Design of.

wing area of sq ft, a span of 84 ft, and a max TOGW oflb. The aerodynamic design of the wing is described in a paper by Wilde and Cormery.7 To allow the slender wing configuration to land and takeoff at an acceptable angle of attack the Concorde took advantage of vortex lift.

They reached the conclusion that winglets can have positive effect on lift/drag, but it is of course highly dependent on the wing shape and profile. From the report: winglets can be designed and aligned in supersonic flow such that little or no performance penalty will be incurred relative to a wing.

Photograph above is the FXL with supersonic laminar flow control experiment (black area on left wing, front) or "glove." The F's large delta wing is similar to the design that likely will be used on the future High-Speed Civil Transport (HSCT), making the FXL an excellent testbed for the laminar flow research project.

In the context of National EXperimental Supersonic Transport program (NEXST), JAXA developed an optimized supersonic high swept wing presenting an extending laminar region, namely a supersonic natural laminar flow wing in and conducted some wind tunnel tests to validate its effect.Cited by: 6.

If the wing moves at high subsonic speed, the curvature-created suction accelerates the flow such that it reaches supersonic speed. Now something odd happens: Supersonic flow accelerates further when subsonic flow would decelerate. This is caused by the change in density which is dominant at supersonic speed.

based on research on wing design for Supersonic Business Jet (SBJ). Goal is to design wing which can generate more lift force and lower the drag[1]. Whenever supersonic jet is discussed most of the time delta shaped wings are considered for the supersonic cruise.

Other times instead of delta back swept wings at high sweet angles areCited by: 1. wing provides shielding from shock waves generated by the inlet and nacelle.

This top-mounted approach introduces a number of issues with inlet design and performance especially with the highly-swept wing configurations common to low-boom designs. An example of one such design is Boeing’s Mach Quiet Experimental Validation ConceptFile Size: 1MB.

The aeroelastic characteristics of the slender wing with store have been studied for several years. However, the nonlinear aeroelastic behaviors of the wing-store system have notAuthor: Yuqian Xu, Dengqing Cao, Chonghui Shao, Huagang Lin.

COREL and W12SC3 are two computer programs useful in the aerodynamic design and analysis of wings for supersonic maneuvering. Both programs use the Super Critical Conical Camber (SC3) concept, in which high supersonic lift coefficients are obtained by controlling cross flow development.

project, using the experimental Bell X-1 research rocket plane, piloted by Charles Chuck Yeager. As jet propulsion opened the prospects of flight in the high-subsonic, tran-sonic, and supersonic flight regimes, however, these and other time-honored tenets of airplane wing design were to undergo radical change.

The classic shape of the air-File Size: 1MB. American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA Cited by: Supersonic flow and shock waves, a manual on the mathematical theory of non-linear wave motion Paperback – by R.

Courant (Author)/5(6).In the present st udy, s ubsonic to supersonic flo ws o ver a delta wing at high angles of attac k and corresponding aerodynamic characteristics o f t he delta wing have been c omputationally.