Download or read book Experimental and Analytical Investigation of Axisymmetric Supersonic Cruise Nozzle Geometry at Mach Numbers Form 0 60 to 1 30 written by George T. Carson and published by . This book was released on 1981 with total page 96 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Experimental and Analytical Investigation of Axisymmetric Supersonic Cruise Nozzle Geometry at Mach Numbers from 0 60 to 1 30 written by and published by . This book was released on 1981 with total page 96 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book The Aeronautical Journal written by and published by . This book was released on 2004 with total page 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 Isolated Performance at Mach Numbers from 0 60 to 2 86 of Several Expendable Nozzle Concepts for Supersonic Applications written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-15 with total page 200 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 Wind Tunnel (at Mach numbers from 2.16 to 2.86) at an angle of attack of 0 deg to determine the isolated performance of several expendable nozzle concepts for supersonic nonaugmented turbojet applications. The effects of centerbody base shape, shroud length, shroud ventilation, cruciform shroud expansion ratio, and cruciform shroud flap vectoring were investigated. The nozzle pressure ratio 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. The shortest nozzle had the best thrust-minus-drag performance at Mach numbers up to 0.95 but was approached in performance by other configurations at Mach numbers of 1.15 and 1.25. At Mach numbers above 1.25, the cruciform nozzle configuration having the same expansion ratio (2.64) as the fixed geometry nozzles had the best thrust-minus-drag performance. Ventilation of the fixed geometry divergent shrouds to the nozzle external boattail flow generally improved thrust-minus-drag performance at Mach numbers from 0.60 to 1.25, but decreased performance above a Mach number of 1.25. Re, Richard J. and Berrier, Bobby L. and Abeyounis, William K. Langley Research Center RTOP 706-17-21-05

Download or read book An Experimental Investigation of the Whistler Nozzle and an Analytical Investigation of a Ring Wing in Supersonic Flow written by Donald L. Weiss and published by . This book was released on 1976 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Modification of a Three dimensional Supersonic Nozzle Analysis and Comparison with Experimental Data written by Allan R. Bishop and published by . This book was released on 1974 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: A computer program previously developed to analyze three-dimensional supersonic nozzles by the method of characteristics has been modified to study less restrictive nozzle geometries and nonuniform inlet conditions. An example indicates that a one-dimensional calculation that uses an averaged initial profile may be significantly in error. A comparison between the analysis and the data from a three-dimensional experiment shows generally good agreement between the two.

Download or read book An Analysis of Supersonic Flow Phenomena in Conical Nozzles by a Method of Characteristics written by Linwood B. Callis and published by . This book was released on 1966 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1986 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Experimental Aerodynamic Characteristics at Mach Numbers from 0 60 to 2 70 of Two Supersonic Cruise Fighter Configurations written by Samuel M. Dollyhigh and published by . This book was released on 1979 with total page 187 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book The Laminar Boundary Layer in Axisymmetric Hypersonic Nozzles with Wall Cooling written by Ross G. Luce and published by . This book was released on 1965 with total page 57 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental and analytic investigation of the influence of wall cooling on conical hypersonic nozzles operated at moderately low Reynolds numbers is reported. The experimental program consisted of nozzle static pressure distributions and impact pressure surveys of a nominal M = 12, 3-inch exit diameter conical nozzle equipped with a coolant tank to allow for the adjustment of the wall temperature. Various coolants (water, freon-dry ice mixture, and liquid nitrogen) were used to provide selected wall temperatures down to 210R. The measurements showed a 25% reduction of the displacement and boundary layer thicknesses when referred to a nozzle equilibrium temperature of 670R. The momentum integral technique was used to formulate a digital computer program to examine the wall cooling effects on hypersonic axisymmetric nozzles. A Pr number of one is assumed. Fourth order velocity and total enthalpy profiles were used. These profiles were adjusted to account for wall temperature, transverse curvature, and pressure gradient. Results from this computer program were confirmed by the experiments. (Author).

Download or read book Experimental Study on the Effects of Nose Geometry on Drag Over Axisymmetric Bodies in Supersonic Flow written by Brian Tyler Brooker and published by . This book was released on 2014 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt: A new nose shape that was determined using the penetration mechanics to have the least penetration drag has been tested in the supersonic wind tunnel of the University of Alabama to determine the aerodynamic characteristics of this nose shape. The aerodynamic drag measured on the new nose shape and on four additional nose shapes are compared to each other. The results show that the new nose shape has the least aerodynamic drag. The measurements were made at Mach numbers ranging from 1.85 to 3.1. This study also required the maintenance of several components of the University of Alabama's 6-inch by 6-inch supersonic wind tunnel and modification of the existing data acquisition programs. These repairs and modifications included the repair and recalibration of the supersonic wind tunnel, repair of the four component force balance, and the modification of the tunnel's control program.

Download or read book Investigation of Axisymmetric and Nonaxisymmetric Nozzles Installed on a 0 10 Scale F 18 Prototype Airplane Model written by Francis J. Capone and published by . This book was released on 1980 with total page 308 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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 An Analytical and Experimental Investigation of the Aeroelastic Stability of Cylindrical Shells at the Subsonic and Supersonic Mach Numbers written by Walter Julian Horn and published by . This book was released on 1972 with total page 318 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Design Tables for Five Axisymmetric Supersonic Nozzles Mach Numbers 1 4 1 6 1 8 2 0 and 2 2 written by William John Rainbird and published by . This book was released on 1953 with total page 4 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Supersonic Nozzle Design of Arbitrary Cross section written by and published by . This book was released on 1988 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation, both theoretical and experimental in nature, has been undertaken to develop a simple method for the design of supersonic nozzles and, indeed, inlets of quite complex shapes from known or calculated axisymmetric flowfields. 1he axisymmetric flowfield is determined using a computer program based on the method of characteristics. Streamlines are calculated by direct integration of the axisymmetric stream function. 7he desired shape is chosen at the exit of the computed axisymmetric nozzle having the desired length and Mach number. Its describing points are then traced along the corresponding streamlines back to the throat. Streamsheets formed by these streamlines define the new shape. Following this approach, two three-dimensional nozzles were designed : one of elliptical cross-section and a two-dimensional wedge. Flows within the two configurations were further simulated using a general purpose three-dimensional CFD code, "PHOENICS", while the elliptical nozzle was subsequently manufactured and submitted to experimental tests. Results from the experimental tests and three-dimensional numerical simulation, as well as predictions of the performance of the nonaxisymmetric nozzles and their axisymmetric counterparts were obtained and compared. Good agreement was achieved between the several components of the study demonstrating that it is possible, using this relatively simple method, to design satisfactory three-dimensional nozzles.