Download or read book Tabulation of Coordinates for Hypersonic Axisymmetric Nozzles Part 1 Analysis and Coordinates for Test Section Mach Numbers of 8 12 and 20 written by Robert J. Cresci and published by . This book was released on 1958 with total page 61 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Tabulation of Coordinates for Hypersonic Axisymmetric Nozzles written by Robert J. Cresci and published by . This book was released on 1958 with total page 74 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Tabulation of Coordinates for Hypersonic Axisymmetric Nozzles written by Robert J. Cresci and published by . This book was released on 1958 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Tabulation of Coordinates for Hypersonic Axisymmetric Nozzles written by and published by . This book was released on 1960 with total page 126 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Tabulation of Coordinates for Hypersonic Axisymmetric Nozzles Part II Coordinates for Test Section Mach Numbers of 6 7 8 5 9 10 14 16 and 18 written by Robert J. Cresci and published by . This book was released on 1960 with total page 126 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book WADC Technical Note written by United States. Wright Air Development Division and published by . This book was released on 1959 with total page 1674 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Technical Note written by and published by . This book was released on 1974 with total page 714 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Journal of the Aero space Sciences written by and published by . This book was released on 1959 with total page 886 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effects of Vibrational Nonequilibrium on the Inviscid Design of an Axisymmetric Nozzle for Hypersonic Flow written by John Benjamin Anders and published by . This book was released on 1975 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Proceedings of the Conference written by and published by . This book was released on 1964-04 with total page 872 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Development and Testing of a New Optimum Design Code for Hypersonic Wind Tunnel Nozzles Including Boundary Layer Turbulence and Real Gas Effects written by Ralph C. Tolle and published by . This book was released on 1996 with total page 274 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Isolated Performance at Mach Numbers From 0 60 to 2 86 of Several Expendable Nozzle Concepts for Supersonic Applications written by Richard J. Re and published by . This book was released on 2001 with total page 202 pages. Available in PDF, EPUB and Kindle. Book excerpt: Investigations have been conducted in the Langley 16-Foot Transonic Tunnel (at Mach numbers from 0.60 to 1.25) and in the Langley Unitary Plan Winf Tunnel (at Mach numbers from 2.16 to 2.86) at an angle of attack of O° to determine the isolated performane of several expendable nozzle concepts for supersonic noaugmented turbojet applications. The effects of centerbody base shape, shroud length, shroud ventilation, cruciform shroud expansion ration, and cruciform shroud flap vectoring were investigated. The nozzle pressure ration range, which was a function of Mach number, was between 1.9 and 11.8 in the 16-Foot Transonic Tunnel and between 7.9 and 54.9 in the Unitary Plan WInd Tunnel. Discharge coefficient, thrust-minus-drag, and the forces and moments generated by vectoring the divergent shroud flaps (for Mach numbers of 0.60 to 1.25 only) of a cruciform nozzle configuration were measured.
Download or read book The Aerodynamic Design and Calibration of an Asymmetric Variable Mach Number Nozzle with Sliding Block for the Mach Number Range 1 27 to 2 75 written by Paige B. Burbank and published by . This book was released on 1951 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: A method of designing an aymmetric, fixed-geometry, variable Mach number nozzle has been developed by using the method of characteristics. A small nozzle conforming to the analytically determined ordinates was a constructed and calibrated over a range of Mach numbers extending from 1.27 to 2.75. The results show the variation in Mach number to be plus or minus 0.02 or less and in the flow direction to be plus or minus 0.2 degrees within the test section. The range of Mach numbers 1.27 to 2.75 was obtained by translating the lower block in a straight line parallel to the test-section center line for a distance of 2.17 test-section heights.
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1966 with total page 1466 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effect of a Variable geometry Diffuser on the Operating Characteristics of a Helium Tunnel Designed for a Mach Number in Excess of 20 written by Patrick J. Johnston and published by . This book was released on 1960 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book progress report no 1 april december 1951 theory and design of a variable mach number corner nozzle written by j.s. murphy, h. buning and published by . This book was released on 1951 with total page 41 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book The Aerodynamic Design of High Mach Number Nozzles Utilizing Axisymmetric Flow with Application to a Nozzle of Square Test Section written by Ivan E. Beckwith and published by . This book was released on 1952 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: A method is given for the design of three-dimensional nozzles utilizing axisymmetric flow to produce uniform flow in a test chamber of arbitrary cross section. The method is applied to obtain the coordinates of a Mach number 10 nozzle for which a square test section is specified. Radial flow is used in a portion of the flow field to reduce the computation time. The remainder of the flow field is computed by the method of characteristics, but a simplified method is used near the axis. Tables which facilitate computation of the radial flow and the flow near the axis are included. Transition streamlines determined from the analytic expressions of Kuno Foelsch are compared with the streamlines obtained from the characteristic net of the Mach number 10 nozzle.
