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High Reynolds Number Test Of A 5 Percent Thick Low Aspect Ratio Semispan Wing In The Langley 03 Meter Transonic Cryogenic Tunnel
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Book Synopsis High-Reynolds-number Test of a 5-percent-thick Low-aspect-ratio Semispan Wing in the Langley 0.3-meter Transonic Cryogenic Tunnel: Wing Pressure Distributions by : Julio Chu
Download or read book High-Reynolds-number Test of a 5-percent-thick Low-aspect-ratio Semispan Wing in the Langley 0.3-meter Transonic Cryogenic Tunnel: Wing Pressure Distributions written by Julio Chu and published by . This book was released on 1990 with total page 204 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781723146596 Total Pages :200 pages Book Rating :4.1/5 (465 download)
Book Synopsis High-Reynolds-Number Test of a 5-Percent-Thick Low-Aspect-Ratio Semispan Wing in the Langley 0.3-Meter Transonic Cryogenic Tunnel by : National Aeronautics and Space Administration (NASA)
Download or read book High-Reynolds-Number Test of a 5-Percent-Thick Low-Aspect-Ratio Semispan Wing in the Langley 0.3-Meter Transonic Cryogenic Tunnel written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-18 with total page 200 pages. Available in PDF, EPUB and Kindle. Book excerpt: A high Reynolds number test of a 5 percent thick low aspect ratio semispan wing was conducted in the adaptive wall test section of the Langley 0.3 m Transonic Cryogenic Tunnel. The model tested had a planform and a NACA 64A-105 airfoil section that is similar to that of the pressure instrumented canard on the X-29 experimental aircraft. Chordwise pressure data for Mach numbers of 0.3, 0.7, and 0.9 were measured for an angle-of-attack range of -4 to 15 deg. The associated Reynolds numbers, based on the geometric mean chord, encompass most of the flight regime of the canard. This test was a free transition investigation. A summary of the wing pressures are presented without analysis as well as adapted test section top and bottom wall pressure signatures. However, the presented graphical data indicate Reynolds number dependent complex leading edge separation phenomena. This data set supplements the existing high Reynolds number database and are useful for computational codes comparison. Chu, Julio and Lawing, Pierce L. Langley Research Center BOUNDARY LAYER SEPARATION; HIGH REYNOLDS NUMBER; LOW ASPECT RATIO WINGS; PRESSURE DISTRIBUTION; WIND TUNNEL TESTS; WING LOADING; AIRFOIL PROFILES; CANARD CONFIGURATIONS; COMPUTATIONAL FLUID DYNAMICS; CRYOGENIC WIND TUNNELS; LEADING EDGES; SUBSONIC SPEED; TRANSONIC WIND TUNNELS; WALL PRESSURE; X-29 AIRCRAFT...
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1989 with total page 1134 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Government Reports Announcements & Index by :
Download or read book Government Reports Announcements & Index written by and published by . This book was released on 1993 with total page 602 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA SP. written by and published by . This book was released on 1993 with total page 360 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Government reports annual index by :
Download or read book Government reports annual index written by and published by . This book was released on 199? with total page 1200 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Monthly Catalog of United States Government Publications by :
Download or read book Monthly Catalog of United States Government Publications written by and published by . This book was released on with total page 1168 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Monthly Catalogue, United States Public Documents by :
Download or read book Monthly Catalogue, United States Public Documents written by and published by . This book was released on 1995 with total page 1208 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aeronautical Engineering written by and published by . This book was released on 1993 with total page 932 pages. Available in PDF, EPUB and Kindle. Book excerpt: A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA).
Book Synopsis AIAA 22nd Fluid Dynamics, Plasma Dynamics & Lasers Conference: 91-1701 - 91-1749 by :
Download or read book AIAA 22nd Fluid Dynamics, Plasma Dynamics & Lasers Conference: 91-1701 - 91-1749 written by and published by . This book was released on 1991 with total page 508 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Surface Pressure Data Obtained on 65 ̊delta Wing Across Reynolds Number and Mach Number Ranges by : Julio Chu
Download or read book Experimental Surface Pressure Data Obtained on 65 ̊delta Wing Across Reynolds Number and Mach Number Ranges written by Julio Chu and published by . This book was released on 1996 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Surface Pressure Data Obtained on 65 Deg Delta Wing Across Reynolds Number and Mach Number Ranges by :
Download or read book Experimental Surface Pressure Data Obtained on 65 Deg Delta Wing Across Reynolds Number and Mach Number Ranges written by and published by . This book was released on 1996 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Pressure Distribution from High Reynolds Number Tests of a NASA SC(3)-0712(B) Airfoil in the Langley 0.3-meter Transonic Cryogenic Tunnel by :
Download or read book Pressure Distribution from High Reynolds Number Tests of a NASA SC(3)-0712(B) Airfoil in the Langley 0.3-meter Transonic Cryogenic Tunnel written by and published by . This book was released on 1985 with total page 416 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis High Reynolds Number Tests of the NASA SC(2)-0012 Airfoil in the Langley 0.3-Meter Transonic Cryogenic Tunnel by : Raymond E. Mineck
Download or read book High Reynolds Number Tests of the NASA SC(2)-0012 Airfoil in the Langley 0.3-Meter Transonic Cryogenic Tunnel written by Raymond E. Mineck and published by . This book was released on 1987 with total page 55 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation at Transonic Speeds of the Loading Over a 45 Degree Sweptback Wing Having an Aspect Ratio of 3, a Taper Ratio of 0.2, and NACA 65A004 Airfoil Sections by : Jack F. Runckel
Download or read book Investigation at Transonic Speeds of the Loading Over a 45 Degree Sweptback Wing Having an Aspect Ratio of 3, a Taper Ratio of 0.2, and NACA 65A004 Airfoil Sections written by Jack F. Runckel and published by . This book was released on 1956 with total page 104 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation at transonic speeds of the loading over a 45 degree sweptback wing having an aspect ratio of 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections has been conducted in the Langley16-foot transonic tunnel. Pressure measurements on the wing-body combination were obtained at angles of attack from 0 to 26 degrees at Mach numbers from 0.80 to 0.98 and from 0 to about 12 degrees at Mach numbers from 1.00 to 1.05. Reynolds number, based on the wing mean aerodynamic chord, varied from 7,000,000 to 8,500,000 over the test Mach number range.
Book Synopsis Transonic Aerodynamic Loading Characteristics of a Wing-body-tail Combination Having 52.5° Sweptback Wing of Aspect Ratio 3 with Conical Wing Camber and Body Indentation for a Design Mach Number [square Root Of] 2 by : Marlowe D. Cassetti
Download or read book Transonic Aerodynamic Loading Characteristics of a Wing-body-tail Combination Having 52.5° Sweptback Wing of Aspect Ratio 3 with Conical Wing Camber and Body Indentation for a Design Mach Number [square Root Of] 2 written by Marlowe D. Cassetti and published by . This book was released on 1961 with total page 104 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been made of the effects of conical wing camber and body indentation according to the supersonic area rule on the aerodynamic wing loading characteristics of a wing-body-tail configuration at transonic speeds. The wing aspect ratio was 3, taper ratio was 0.1, and quarter-chord-line sweepback was 52.5° with 3-percent-thick airfoil sections. The tests were conducted in the Langley 16-foot transonic tunnel at Mach numbers from 0.80 to 1.05 and at angles of attack from 0° to 14°, with Reynolds numbers based on mean aerodynamic chord varying from 7 x 106 to 8 x 106. Conical camber delayed wing-tip stall and reduced the severity of the accompanying longitudinal instability but did not appreciably affect the spanwise load distribution at angles of attack below tip stall. Body indentation reduced to transonic chordwise center-of-pressure travel from about 8 percent to 5 percent of the mean aerodynamic chord.
Book Synopsis The Cryogenic Wind-tunnel Concept for High Reynolds Number Testing by :
Download or read book The Cryogenic Wind-tunnel Concept for High Reynolds Number Testing written by and published by . This book was released on 1974 with total page 100 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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