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A Wind Tunnel Investigation Of Three Naca 1 Series Inlets At Mach Numbers Up To 092
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Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781722915704 Total Pages :184 pages Book Rating :4.9/5 (157 download)
Book Synopsis A Wind Tunnel Investigation of Three NACA 1-Series Inlets at Mach Numbers Up To 0. 92 by : National Aeronautics and Space Administration (NASA)
Download or read book A Wind Tunnel Investigation of Three NACA 1-Series Inlets at Mach Numbers Up To 0. 92 written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-17 with total page 184 pages. Available in PDF, EPUB and Kindle. Book excerpt: Pressure distributions on three NACA 1-series inlets have been obtained in the Langley 16-Foot Transonic Tunnel. The cowl diameter ratio (ratio of cowl highlight diameter to cowl maximum diameter) was 0.85 for all three inlets. The cowl length ratio (ratio of cowl length to cowl maximum diameter) was 1.0 for two of the inlets (NACA 1-85-100) and 0.439 for the other (NACA 1-85-43.9) inlet. One of the inlets with a cowl length ratio of 1.0 had an internal contraction ratio (ratio of highlight area to throat area) of 1.009 and the other had a contraction ratio of 1.250. The inlet with a cowl length ratio of 0.439 also had an internal contraction ratio of 1.250. All three inlets had longitudinal rows of static pressure orifices on the top and bottom external cowl surfaces. The inlet with a contraction ratio of 1.009 also had a row of static pressure orifices on the side of the cowl (external surface). The two inlets with a contraction ratio of 1.250 had a longitudinal row of static pressure orifices on the diffuser surface. Re, Richard J. and Abeyounis, William K. Langley Research Center WIND TUNNEL TESTS; PRESSURE DISTRIBUTION; STATIC PRESSURE; ENGINE INLETS; AIRCRAFT ENGINES; MACH NUMBER; ANGLE OF ATTACK; SUBSONIC FLOW; CONTRACTION; NACELLES; FOREBODIES; MASS FLOW; PRESSURE MEASUREMENT; AXISYMMETRIC BODIES...
Book Synopsis A Wind Tunnel Investigation of Three NACA 1-Series Inlets at Mach Numbers Up to 0.92 by :
Download or read book A Wind Tunnel Investigation of Three NACA 1-Series Inlets at Mach Numbers Up to 0.92 written by and published by . This book was released on 1996 with total page 188 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Wind Tunnel Investigation of Three NACA 1-series Inlets at Mach Numbers Up to 0.92 by : Richard J. Re
Download or read book A Wind Tunnel Investigation of Three NACA 1-series Inlets at Mach Numbers Up to 0.92 written by Richard J. Re and published by . This book was released on 1996 with total page 180 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Wind Tunnel Investigation of Three NASA 1-series Inlets at Mach Numbers Up to 0.92 by : Richard J. Re
Download or read book A Wind Tunnel Investigation of Three NASA 1-series Inlets at Mach Numbers Up to 0.92 written by Richard J. Re and published by . This book was released on 1996 with total page 180 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An investigation of several NACA 1-series inlets at Mach numbers from 0.4 to 1.29 for mass-flow ratios near 1.0 by : Richard J. Re
Download or read book An investigation of several NACA 1-series inlets at Mach numbers from 0.4 to 1.29 for mass-flow ratios near 1.0 written by Richard J. Re and published by . This book was released on 1976 with total page 116 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Investigation of Several NACA 1-series Axisymmetric Inlets at Mach Numbers from 0.4 to 1.29 by : Richard J. Re
Download or read book An Investigation of Several NACA 1-series Axisymmetric Inlets at Mach Numbers from 0.4 to 1.29 written by Richard J. Re and published by . This book was released on 1974 with total page 150 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Technical Memorandum written by and published by . This book was released on 1994 with total page 492 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wind Tunnel Investigation of Three Axisymmetric Cowls of Different Lengths at Mach Numbers from 0.60 to 0.92 by : Richard J. Re
Download or read book Wind Tunnel Investigation of Three Axisymmetric Cowls of Different Lengths at Mach Numbers from 0.60 to 0.92 written by Richard J. Re and published by . This book was released on 1993 with total page 292 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 1961 with total page 1878 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Research Abstracts and Reclassification Notice by : United States. National Advisory Committee for Aeronautics
Download or read book Research Abstracts and Reclassification Notice written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1954 with total page 508 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Research Abstracts by : United States. National Advisory Committee for Aeronautics
Download or read book Research Abstracts written by United States. National Advisory Committee for Aeronautics and published by . This book was released on with total page 442 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wind Tunnel Investigation of a 1/9-scale Boeing Company Amsa Airplane-inlet Model at Transonic and Supersonic Mach Numbers by : D. C. Baker
Download or read book Wind Tunnel Investigation of a 1/9-scale Boeing Company Amsa Airplane-inlet Model at Transonic and Supersonic Mach Numbers written by D. C. Baker and published by . This book was released on 1967 with total page 61 pages. Available in PDF, EPUB and Kindle. Book excerpt: A 1/9-scale model of the AMSA was tested in the Propulsion Wind Tunnel, Transonic (16T) and Propulsion Wind Tunnel, Supersonic (16S) of the Propulsion Wind Tunnel Facility (PWT). The test vehicle consisted of an airplane model and two pressure-instrumented inlet nacelles. Airplane model variations representing three-engine and four-engine configurations were tested with the two engine nacelles representing either two-thirds or one-half of the full airplane configuration. The three-engine configuration consisted of one pylon-mounted nacelle under the left wing and one tail-mounted nacelle above the fuselage on the airplane vertical centerline. The symmetrical four-engine configurations had either two adjacent nacelles suspended under the left wing or one forward nacelle under the left wing and one nacelle mounted aft on the left side of the fuselage near the tail. Data were obtained at free-stream Mach numbers from 0.60 to 2.30 to determine the performance characteristics of the inlets, and the effects of mutual interactions of inlets and airplane surfaces. The model attitude was varied throughout an angle-of-attack range of -4 to +11 deg and yaw angles of plus or minus 4 deg.
Download or read book Applied Mechanics Reviews written by and published by . This book was released on 1968 with total page 700 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 1992 with total page 324 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Tests of a Small-scale NACA Submerged Inlet at Transonic Mach Numbers by : L. Stewart Rolls
Download or read book Tests of a Small-scale NACA Submerged Inlet at Transonic Mach Numbers written by L. Stewart Rolls and published by . This book was released on 1950 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: The pressure-recovery characteristics at the vertical center line of an NACA submerged inlet of aspect ratio 5 have been measured in the Mach number range 0.60 to 1.08 by the wing-flow method. The variation of ram-recovery ratio determined from measurements at the center line of the inlet with test station Mach number is presented for mass-flow ratios of 0.30 to 0.60.
Book Synopsis NASA Langley Scientific and Technical Information Output: 1996 by :
Download or read book NASA Langley Scientific and Technical Information Output: 1996 written by and published by . This book was released on 1997 with total page 180 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Report by : United States. National Advisory Committee for Aeronautics
Download or read book Report written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1949 with total page 118 pages. Available in PDF, EPUB and Kindle. Book excerpt:
