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Wednesday, July 29, 2020 | History

2 edition of Flight, wind-tunnel, and computational fluid dynamics comparison for cranked arrow wing (F-16XL-1) at subsonic and transonic speeds found in the catalog.

Flight, wind-tunnel, and computational fluid dynamics comparison for cranked arrow wing (F-16XL-1) at subsonic and transonic speeds

Flight, wind-tunnel, and computational fluid dynamics comparison for cranked arrow wing (F-16XL-1) at subsonic and transonic speeds

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  • 24 Currently reading

Published by National Aeronautics and Space Administration, Langley Research Center, Available from NASA Center for AeroSpace Information (CASI) in Hampton, Va, Hanover MD .
Written in English

    Subjects:
  • Aerodynamic characteristics.,
  • Computational fluid dynamics.,
  • Subsonic speed.,
  • Transonic speed.,
  • Wind tunnel tests.,
  • Wing profiles.,
  • Geometry.,
  • Flight tests.,
  • Data integration.

  • Edition Notes

    Other titlesFlight, wind tunnel, and computational fluid dynamics comparison for cranked arrow wing (F-16XL-1) at subsonic and transonic speeds.
    StatementJohn E. Lamar ... [et al.].
    SeriesNASA/TP -- 2001-210629., NASA technical paper -- 210629.
    ContributionsLamar, John E., Langley Research Center.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL18182589M

    to perform a flight dynamics analysis of the UCAV configuration. The purpose of this analysis is to compare the flying qualities as derived from wind tunnel data with the results determined on the basis of data from VSAERO, a low-fidelity aerodynamic tool used in preliminary aircraft design. /,67 2) 6. Fixed and Flapping Wing Aerodynamics for Micro Air Vehicle Applications Computation of Aerodynamic Characteristics of a Micro Air Vehicle. I Introduction. direction distribution drag dynamic edge effect efficiency element Engineering equations Experimental experiments Figure flapping wing flight flow Fluid force frequency function 5/5(1).

    FXL WING PRESSURE DISTRIBUTIONS AND SHOCK FENCE RESULTS FROM MACH TO MACH , Technical Memorandum Authors: Stephen F. Landers, John A. Saltzman and Lisa J. Bjarke Report Number: NASA-TM Performing Organization: NASA Dryden Flight Research Center, Edwards, CA Abstract: Chordwise pressure distributions were obtained in-flight on the upper and . Computational Fluid Dynamics J.D. Anderson Jr. (auth.), John F. Wendt (eds.) The book provides an elementary tutorial presentation on computational fluid dynamics (CFD), emphasizing the fundamentals and surveying a variety of solution techniques whose applications range from low speed incompressible flow to hypersonic flow.

    AERODYNAMIC PITCH-UP OF CRANKED ARROW WINGS: ESTIMATION, TRIM, AND CONFIGURATION DESIGN by Alexander M. Benoliel Committee Chairman: William H. Mason Aerospace & Ocean Engineering (ABSTRACT) Low aspect ratio, highly-swept cranked arrow wing planforms are often proposed for high-speed civil Size: KB. Aerodynamics - Free download as Powerpoint Presentation .ppt /.pptx), PDF File .pdf), Text File .txt) or view presentation slides online.


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Flight, wind-tunnel, and computational fluid dynamics comparison for cranked arrow wing (F-16XL-1) at subsonic and transonic speeds Download PDF EPUB FB2

Flight, Wind-Tunnel, and Computational Fluid Dynamics Comparison for Cranked Arrow Wing (FXL-1) at Subsonic and Transonic Speeds Article (PDF Available) April with Reads How we. Flight, Wind-Tunnel, and Computational Fluid Dynamics Comparison for Cranked Arrow Wing (FXL-1) at Subsonic and Transonic Speeds John E.

Lamar, Clifford J. Obara, and Bruce D. Fisher Langley Research Center, Hampton, Virginia David F. Fisher Dryden Flight Research Center, Edwards, California February Geometrical, flight, computational fluid dynamics (CFD), and wind-tunnel studies for the FXL-1 airplane are summarized over a wide range of test conditions.

Details are as follows: (1) For geometry, the upper surface of the airplane and the numerical surface description compare reasonably well.

Get this from a library. Flight, wind-tunnel, and computational fluid dynamics comparison for cranked arrow wing (FXL-1) at subsonic and transonic speeds. BibTeX @MISC{Clifford01flight,wind-tunnel, author = {John Lamar Clifford and Clifford J.

Obara and Bruce D. Fisher and David F. Fisher}, title = {Flight, And computational fluid dynamics comparison for cranked arrow wing book, and Computational Fluid Dynamics Comparison for Cranked Arrow Wing (FXL-1) at Subsonic and Transonic Speeds}, year = {}}.

Flight Test Results for the FXL With a Digital Flight Control System () +Read more Flight, Wind-Tunnel, and Computational Fluid Dynamics Comparison for Cranked Arrow Wing (FXL-1) at Subsonic and Transonic Speeds () + Read more Measurements of the Basic SR Airplane Near-Field Signature () + Read more Dynamic Ground Effect for a Cranked Arrow Wing Airplane.

This paper provides a brief history of the FXL-1 aircraft, its role in the High Speed Research program and how it was morphed into the Cranked Arrow Wing Aerodynamics Project. Various flight, wind-tunnel and Computational Fluid Dynamics data sets were generated as part of the project.

These unique and open flight datasets for surface Cited by: program and how it was morphed into the Cranked Arrow Wing Aerodynamics Project (CAWAP). Various flight, wind-tunnel and Computational Fluid Dynamics (CFD) data sets were generated during the CAWAP2. These are described and sample data comparisons given.

This is followed by a description of how the project becameFile Size: 2MB. program and how it was morphed into the Cranked Arrow Wing Aerodynamics Project (CAWAP). Various flight, wind-tunnel and Computational Fluid Dynamics (CFD) Cited by: Flight, Wind-Tunnel, and Computational Fluid Dynamics Comparison for Cranked Arrow Wing (FXL-1) at Subsonic and Transonic Speeds.

By John Lamar Clifford, Clifford J. Obara, Bruce D. Fisher and David F. Fisher. Abstract. this report. A highly integrated effort was required in order to compare these data.

To that end, a by-product of this. [1] Lamar J. E., Obara C. J., Fisher B. and Fisher D. F., “ Flight, Wind-Tunnel, and Computational Fluid Dynamics Comparison for Cranked Arrow Wing (FXL-1) at Subsonic and Transonic Speeds,” NASA TP, Feb.

Google ScholarCited by: 1. Flight, Wind-Tunnel, and Computational Fluid Dynamics Comparison for Cranked Arrow Wing (FXL-1) at Subsonic and Transonic Speeds. By Bruce D. Fisher, Clifford J. Obara, John E. Lamar and David F. Fisher.

Abstract. The data contained on this CD are a supplement to NASA/TP published in February This CD replaces a web-site. The prior efforts were identified as the Cranked-Arrow Wing Aerodynamics Project International.

[1] Lamar J. E., Obara C. J., Fisher B. and Fisher D. F., “ Flight, Wind-Tunnel, and Computational Fluid Dynamics Comparison for Cranked Arrow Wing (FXL-1) at Subsonic and Transonic Speeds,” NASA TPFeb.

Cited by: 1. Testing a refueling probe in a wind tunnel. Lots of videos show the problems occurring during air refuling to overcome these kinds of problems wind tunnel tests can help in knowing the optimum speeds of the refuling aircrat and the the refueled one in addition to the affects of cross winds.

Different flight speeds affect the refueling basket, the. Applied Computational Aerodynamics This computational aerodynamics (CA) textbook is written at the undergradu-ate level, based on years of teaching focused on developing the engineering skills required to become an intelligent user of aerodynamic codes, unlike most avail-able books which focus on learning how to write codes.

This is done by taking. Computational fluid dynamics (CFD) has had a profound impact on the aircraft design process in the past four decades and is partially responsible for the reduction in the amount of wind-tunnel testing that was conducted during the same periodBecause computer speed by: 6.

Wind tunnel tests are done for the following This is a helpful book (AIRCRAFT DESIGN PROJECTS) for undergraduate students working on an aircraft design project (final year project)for the first time.

Computational fluid dynamics can also be used to introduce new concepts such as. A review of the steps taken to establish an international virtual laboratory (VL) at the NASA Langley Research Center for aerodynamic prediction and c Cited by: Computational fluid dynamics: the basics with applications John Anderson This pioneering text provides an excellent introduction to CFD at the senior level in aerospace and mechanical engineering, and to some extent, chemical and civil engineering.

This is a CFD Analysis of a Spoiler / Wing from an automobile. This DATA is used in the static and dynamic structural analysis. Cranked Arrow Wing (FXL-1) Flight Flow Physics with CFD Predictions at Subsonic and Transonic Speeds John E. Lamar NASA Langley Research Center, M.S. Hampton, VirginiaUSA Summary The CFD modeling used has produced reasonably good File Size: 4MB.Computational fluid dynamics (CFD) is only of interest to the industry if it helps to minimize the cost and maximize certainty and speed for a good design.

The numerical solutions obtained here have been compared with the wind tunnel test data for the computational fluid dynamics (CFD) code validation. Parallel Computational Fluid.efficiency of the applied computational analysis gives satisfactory results compared, when possible, against the published data of verified experiments.

This paper studies the separation of a generic store released from a typical wing pylon of a fighter aircraft at Mach number A collection of computational fluid dynamic toolsFile Size: KB.