Download or read book An Experimental Investigation of the Mach Two Nozzle UCLA Supersonic Wind Tunnel written by William F. MacInnes and published by . This book was released on 1954 with total page 108 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Experimental Investigation of the Subsonic High altitude Operation of the NASA Lewis 10 by 10 foot Supersonic Wind Tunnel written by and published by . This book was released on 1988 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Register of the University of California written by University of California (1868-1952) and published by . This book was released on 1955 with total page 1426 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Supersonic Investigation of Two Dimensional Hypersonic Exhaust Nozzles written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-12 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was conducted in the NASA Lewis 10 x 10 ft supersonic Wind Tunnel to determine the performance characteristics of 2D hypersonic exhaust nozzles/afterbodies at low supersonic conditions. Generally, this type of application requires a single expansion ramp nozzle (SERN) that is highly integrated with the airframe of the hypersonic vehicle. At design conditions (hypersonic speeds), the nozzle generally exhibits acceptable performance. At off-design conditions (transonic to mid-supersonic speeds), nozzle performance of a fixed geometry configuration is generally poor. Various 2-D nozzle configurations were tested at off-design conditions from Mach 2.0 to 3.5. Performance data is presented at nozzle pressure ratios from 1 to 35. Jet exhaust was simulated with high-pressure air. To study performance of different geometries, nozzle configurations were varied by interchanging the following model parts: internal upstream contour, expansion ramp, sidewalls, and cowl. Carboni, Jeanne D. and Shyne, Rickey J. and Leavitt, Laurence D. and Taylor, John G. and Lamb, Milton Glenn Research Center; Langley Research Center RTOP 763-01-21...

Download or read book Supersonic Wind Tunnel Nozzles written by Stephen W. D. Wolf and published by . This book was released on 1990 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Summary written by University of California, Los Angeles. Dept. of Engineering and published by . This book was released on 1950 with total page 980 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Preliminary Investigation of a Variable Mach Number Two dimensional Supersonic Tunnel of Fixed Geometry written by William J. Nelson and published by . This book was released on 1949 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Experimental Investigation of a Mach 5 Isentropic Spike Inlet at and Below Design Speed written by Leonard E. Stitt and published by . This book was released on 1959 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Experimental Investigation of the Condensation of Air in a Mach 7 2 Wind Tunnel written by Kenneth C. Rathbun and published by . This book was released on 1951 with total page 170 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Diffuser Efficiency and Flow Process of Supersonic Wind Tunnels with Free Jet Test Section written by Rudolf Hermann and published by . This book was released on 1950 with total page 90 pages. Available in PDF, EPUB and Kindle. Book excerpt: In the wind tunnel arrangement under consideration, the air leaves the Laval nozzle as a free jet and is recaptured by the diffuser, which is of the convergent-divergent design. A theoretical analysis of the flow process through this type of supersonic wind tunnel is presented and the diffuser efficiency is calculated for the case of equilibrium between test chamber pressure and pressure in the nozzle exit, assuming one-dimensional, in viscous, steady flow. Using the basic equations of continuity, energy and momentum flux through a bounding surface, an exact solution of the problem is obtained, which is applicable up to Mach number infinite. One of the basic results is, that in the recapturing zone of the diffuser a transition occurs from supersonic to subsonic flow, which is followed by an acceleration in the convergent portion up to sonic velocity at the second throat. The transition is not a normal shock and involves a total pressure loss greater than that of a normal shock at the test section Mach number. A mathematical solution with supersonic velocity after the transition process has no physical existence. A comprehensive comparison of the analytical results with available experiments in supersonic wind tunnels up to Mach number 4.4 regarding diffuser efficiency and second throat area shows good agreement.

Download or read book An Experimental and Analytical Investigation of Critical Design Paramenters for High Mach Number Open jet Supersonic Wind Tunnel written by Ohio State University. Research Foundation and published by . This book was released on 1954 with total page 78 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book NASA Contractor Report written by and published by . This book was released on 1990 with total page 522 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Applied Mechanics Reviews written by and published by . This book was released on 1962 with total page 1116 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Experimental Investigation of the Partial Admission Performance Characteristics of a Single stage Mach 2 Supersonic Turbine written by Thomas P. Moffitt and published by . This book was released on 1959 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Part I The Effect of a Simple Throat Distortion on the Downstream Flow in a Hypersonic Wind Tunnel Nozzle written by Robert E. Oliver and published by . This book was released on 1957 with total page 94 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book An Experimental and Analytical Investigation of Critical Design Parameters for High Mach Number Open jet Supersonic Wind Tunnels written by J. D. Lee and published by . This book was released on 1954 with total page 39 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book An Investigation of the Model Blockage for Wind Tunnels at Mach Numbers 1 5 to 19 5 written by C. J. Schueler and published by . This book was released on 1960 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation of the test section flow blockage characteristics was conducted in the 12- by 12 inch supersonic wind tunnel (Tunnel E-1) of the Von Karman Gas Dynamics Facility (AEDC). The purpose of the tests was to determine whether a method of predicting the maximum size model which will permit the establishment of supersonic flow, based on the model frontal area and bow shock-wave strength, is applicable over a wide range of Mach numbers. The tests conducted over the Mach number range from 1.5 to 5 using test models consisting of 15, 20, and 20 degrees half-angle cones, cone-cylinder combinations, and a series of discs. The inadequacy of the one dimensional, normal shock theory for predicting allowable model sizes was reconfirmed in these tests. Furthermore a correlation based on shock wave strength and model frontal area was found to be suitable only over a limited range of Mach numbers. Permissible hemisphere-cylinder model sizes from several wind tunnels covering the Mach number range from 1.5 to 19.5 are also presented.