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F 16xl 2 Supersonic Laminar Flow Control Flight Test Experiment
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Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781721931125 Total Pages :262 pages Book Rating :4.9/5 (311 download)
Book Synopsis F-16xl-2 Supersonic Laminar Flow Control Flight Test Experiment by : National Aeronautics and Space Administration (NASA)
Download or read book F-16xl-2 Supersonic Laminar Flow Control Flight Test Experiment written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-27 with total page 262 pages. Available in PDF, EPUB and Kindle. Book excerpt: The F-16XL-2 Supersonic Laminar Flow Control Flight Test Experiment was part of the NASA High-Speed Research Program. The goal of the experiment was to demonstrate extensive laminar flow, to validate computational fluid dynamics (CFD) codes and design methodology, and to establish laminar flow control design criteria. Topics include the flight test hardware and design, airplane modification, the pressure and suction distributions achieved, the laminar flow achieved, and the data analysis and code correlation. Anders, Scott G. and Fischer, Michael C. Langley Research Center RTOP 537-07-23-21
Book Synopsis F-16XL-2 Supersonic Laminar Flow Control Flight Test Experiment by :
Download or read book F-16XL-2 Supersonic Laminar Flow Control Flight Test Experiment written by and published by . This book was released on 1999 with total page 268 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Boundary-layer Transition Results from the F-16XL-2 Supersonic Laminar Flow Control Experiment by : Laurie A. Marshall
Download or read book Boundary-layer Transition Results from the F-16XL-2 Supersonic Laminar Flow Control Experiment written by Laurie A. Marshall and published by . This book was released on 1999 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt: A variable-porosity suction glove has been flown on the F-16XL-2 aircraft to demonstrate the feasibility of this technology for the proposed High-Speed Civil Transport (HSCT). Boundary-layer transition data have been obtained on the titanium glove primarily at Mach 2.0 and altitudes of 53,000-55,000 ft. The objectives of this supersonic laminar flow control flight experiment have been to achieve 50- to 60-percent-chord laminar flow on a highly swept wing at supersonic speeds and to provide data to validate codes and suction design. The most successful laminar flow results have not been obtained at the glove design point (Mach 1.9 at an altitude of 50,000 ft). At Mach 2.0 and an altitude of 53,000 ft, which corresponds to a Reynolds number of 22.7 multiplied by 10[factor 6], optimum suction levels have allowed long runs of a minimum of 46-percent-chord laminar flow to be achieved. This paper discusses research variables that directly impact the ability to obtain laminar flow and techniques to correct for these variables.
Book Synopsis Overview of Supersonic Laminar Flow Control Research on the F-16XL Ships 1 and 2 by :
Download or read book Overview of Supersonic Laminar Flow Control Research on the F-16XL Ships 1 and 2 written by and published by . This book was released on 1992 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Flight, Wind-Tunnel, and Computational Fluid Dynamics Comparison for Cranked Arrow Wing (F-16XL-1) at Subsonic and Transonic Speeds by : John E. Lamar
Download or read book Flight, Wind-Tunnel, and Computational Fluid Dynamics Comparison for Cranked Arrow Wing (F-16XL-1) at Subsonic and Transonic Speeds written by John E. Lamar and published by . This book was released on 2001 with total page 170 pages. Available in PDF, EPUB and Kindle. Book excerpt: Geometrical, flight, computational fluid dynamics (CFD), and wind-tunnel studies for the F-16XL-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. (2) For flight, CFD, and wind-tunnel surface pressures, the comparisons are generally good at low angles of attack at both subsonic and transonic speeds; however, local differences are present. In addition, the shock location at transonic speeds from wind-tunnel presure contours is near the aileron hinge line and generally is in correlative agreement with flight results.
Book Synopsis First Annual High-Speed Research Workshop, Part 4 by :
Download or read book First Annual High-Speed Research Workshop, Part 4 written by and published by . This book was released on 1992 with total page 420 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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Book Synopsis F-16XL Wing Pressure Distributions and Shock Fence Results from Mach 1.4 to Mach 2.0 by : Stephen F. Landers
Download or read book F-16XL Wing Pressure Distributions and Shock Fence Results from Mach 1.4 to Mach 2.0 written by Stephen F. Landers and published by . This book was released on 1997 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt: Chordwise pressure distributions were obtained in-flight on the upper and lower surfaces of the F-16XL ship 2 aircraft wing between Mach 1.4 and Mach 2.0. This experiment was conducted to determine the location of shock waves which could compromise or invalidate a follow-on test of a large chord laminar flow control suction panel. On the upper surface, the canopy closure shock crossed an area which would be covered by a proposed laminar flow suction panel. At the laminar flow experiment design Mach number of 1.9, 91 percent of the suction panel area would be forward of the shock. At Mach 1.4, that value reduces to 65 percent. On the lower surface, a shock from the inlet diverter would impinge on the proposed suction panel leading edge. A chordwise plate mounted vertically to deflect shock waves, called a shock fence, was installed between the inlet diverter and the leading edge. This plate was effective in reducing the pressure gradients caused by the inlet shock system.
Book Synopsis Flow and Noise Control: Review and Assessment of Future Directions by : Russell H. Thomas
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Book Synopsis A Flight Test of Laminar Flow Control Leading-edge Systems by :
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Book Synopsis NASA's Contributions to Aeronautics, Volume 2, Flight Environment ..., NASA/SP-2010-570-Vol 2, 2010, * by :
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Author :United States. Congress. House. Committee on Appropriations. Subcommittee on VA, HUD, and Independent Agencies Publisher : ISBN 13 : Total Pages :1052 pages Book Rating :4.F/5 ( download)
Book Synopsis Departments of Veterans Affairs and Housing and Urban Development, and Independent Agencies Appropriations for 1997 by : United States. Congress. House. Committee on Appropriations. Subcommittee on VA, HUD, and Independent Agencies
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Book Synopsis Aeronautics and Space Report of the President by : United States. President
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Book Synopsis Aeronautics and Space Report of the President ... Activities by : United States. President
Download or read book Aeronautics and Space Report of the President ... Activities written by United States. President and published by . This book was released on 1990 with total page 198 pages. Available in PDF, EPUB and Kindle. Book excerpt:
