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Thrust Coefficients Of Low Thrust Nozzles
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Book Synopsis Thrust Coefficients of Low-thrust Nozzles by : Ernie W. Spisz
Download or read book Thrust Coefficients of Low-thrust Nozzles written by Ernie W. Spisz and published by . This book was released on 1965 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: The performance losses associated with small nozzles operating at low propellant flow rates were investigated experimentally with a resistance-heated hydrogen thrustor. Data were obtained for seven different nozzles covering the range of nozzle area ratio from 25 to 150, hydrogen propellant flow rates of 0.5x10 to the -4, 1.0x10 to the -4, and 2.5x10 to the -4 pound per second, and propellant temperatures from 530 to 4000 R. The nozzle losses, as determined by the difference between the one-dimensional isentropic thrust coefficient and the measured thrust coefficient, were correlated in terms of the throat Reynolds number and nozzle area ratio. At low throat Reynolds number, the nozzle losses were sufficiently large to result in measured thrust coefficients less than the values calculated for isentropic flow through a choked orifice. Results show that large area ratios are not required for achieving maximum thrust for nozzles with low throat Reynolds number (
Book Synopsis Internal Performance Characteristics of Short Convergent-divergent Exhaust Nozzles Designed by the Method of Characteristics by : H. George Krull
Download or read book Internal Performance Characteristics of Short Convergent-divergent Exhaust Nozzles Designed by the Method of Characteristics written by H. George Krull and published by . This book was released on 1956 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: An evaluation of the internal performance characteristics of short nozzles designed by the method of characteristics was obtained over a range of nozzle pressure ratios from 1.5 to 22.
Book Synopsis Thrust Coefficients, Thrust Deflection Angles, and Nondimensional Moments for Nozzles with Oblique Exit Planes by : William W. Phillips
Download or read book Thrust Coefficients, Thrust Deflection Angles, and Nondimensional Moments for Nozzles with Oblique Exit Planes written by William W. Phillips and published by . This book was released on 1968 with total page 549 pages. Available in PDF, EPUB and Kindle. Book excerpt: Nozzles with oblique exit planes, scarfed nozzles, are encountered in aerospace applications such as reaction control and thrust reversal systems. This document provides thrust coefficient, thrust deflection angle, and nondimensional turning moment data for scarfed conical nozzles on machine- generated graphs. Based on one-dimensional isentropic flow of a perfect gas, the data cover specific heat ratios from 1.18 to 1.40, nozzle half-angles from 5 to 25 degrees, scarf angles from 10 to 60 degrees, area ratios at the upstream scarf point from 1.5 to 15, and ratios of chamber pressure to ambient pressure from 20 to infinity (vacuum).
Book Synopsis Performance of Several Conical Convergent-divergent Rocket-type Exhaust Nozzles by : C. E. Campbell
Download or read book Performance of Several Conical Convergent-divergent Rocket-type Exhaust Nozzles written by C. E. Campbell and published by . This book was released on 1960 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was conducted to obtain nozzle performance data with relatively large-scale models at pressure ratios as high as 120. Conical convergent-divergent nozzles with divergence angles alpha of 15, 25, and 29 deg. were each tested at area ratios of approximately 10, 25, and 40. Heated air (1200 F) was supplied at the nozzle inlet at pressures up to 145 pounds per square inch absolute and was exhausted into quiescent air at pressures as low as 1.2 pounds per square inch absolute. Thrust ratios for all nozzle configurations are presented over the range of pressure ratios attainable and were extrapolated when possible to design pressure ratio and beyond. Design thrust ratios decreased with increasing nozzle divergence angle according to the trend predicted by the (1 + cos alpha)/2 parameter. Decreasing the nozzle divergence angle resulted in sizable increases in thrust ratio for a given surface-area ratio (nozzle weight), particularly at low nozzle pressure ratios. Correlations of the nozzle static pressure at separation and of the average static pressure downstream of separation with various nozzle parameters permitted the calculation of thrust in the separated-flow region from unseparated static-pressure distributions. Thrust ratios calculated by this method agreed with measured values within about 1 percent.
Book Synopsis Comparison of Theoretical and Experimental Thrust Performance of a 1030:1 Area Ratio Rocket Nozzle at a Chamber Pressure of 2413 KN/m2 (350 Psia) by : Tamara A. Smith
Download or read book Comparison of Theoretical and Experimental Thrust Performance of a 1030:1 Area Ratio Rocket Nozzle at a Chamber Pressure of 2413 KN/m2 (350 Psia) written by Tamara A. Smith and published by . This book was released on 1987 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Static Thrust of an Annular Nozzle with a Concave Central Base by : Blake W. Corson (Jr)
Download or read book Static Thrust of an Annular Nozzle with a Concave Central Base written by Blake W. Corson (Jr) and published by . This book was released on 1960 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: A static test of an annular nozzle with a concave central base, producing a jet in which tangents to the jet streamlines at the exit converged toward a region on the axis of symmetry downstream of the exit, has indicated good thrust performance. A value of nozzle-flow coefficient only slightly less than unity indicates the internal loss to be small. Pressures on the concave central base are relatively large and positive, and a predictable portion of the total thrust of the jet is exerted on the central base.
Book Synopsis Investigation of Low-Reynolds-Number Rocket Nozzle Design Using PNS-Based Optimization Procedure by :
Download or read book Investigation of Low-Reynolds-Number Rocket Nozzle Design Using PNS-Based Optimization Procedure written by and published by . This book was released on 1996 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Thrust Performance of a High-area-ratio Rocket Nozzle by : Albert J. Pavli
Download or read book Experimental Thrust Performance of a High-area-ratio Rocket Nozzle written by Albert J. Pavli and published by . This book was released on 1987 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The performance of low thrust (0.05N) Venturi Nozzles by : B. P. Day
Download or read book The performance of low thrust (0.05N) Venturi Nozzles written by B. P. Day and published by . This book was released on 1965 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: An account is given of experiments to determine the performance under transient and steady state conditions of a 0.05 Newtons thrust nozzle for use with propane gas. It is shown that, with the inclusion of viscous effects in the flow equations, which is necessary at low thrust levels, the nozzle achieved the design performance at the operating plenum pressure, but at lower pressures the performance deteriorated. (Author).
Book Synopsis Low Reynolds Number Nozzle Flow Study by : Margaret V. Whalen
Download or read book Low Reynolds Number Nozzle Flow Study written by Margaret V. Whalen and published by . This book was released on 1987 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Study of Effects of Geometric Variables on Performance of Contoured Rocket Engine Exhaust Nozzles by : Harry E. Bloomer
Download or read book Experimental Study of Effects of Geometric Variables on Performance of Contoured Rocket Engine Exhaust Nozzles written by Harry E. Bloomer and published by . This book was released on 1962 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Computational Prediction of Isolated Performance of an Axisymmetric Nozzle at Mach Number 0.90 by : John R. Carlson
Download or read book Computational Prediction of Isolated Performance of an Axisymmetric Nozzle at Mach Number 0.90 written by John R. Carlson and published by . This book was released on 1994 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Off-design Performance of Two Isentropic Plug Nozzles Designed for a Pressure Ratio of 16.5 by : Bobby L. Berrier
Download or read book Off-design Performance of Two Isentropic Plug Nozzles Designed for a Pressure Ratio of 16.5 written by Bobby L. Berrier and published by . This book was released on 1967 with total page 44 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 1977 with total page 790 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Internal Performance of Several Divergent-shroud Ejector Nozzles with High Divergence Angles by : Arthur M. Trout
Download or read book Internal Performance of Several Divergent-shroud Ejector Nozzles with High Divergence Angles written by Arthur M. Trout and published by . This book was released on 1957 with total page 70 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Adm Nasa Publisher :Independently Published ISBN 13 :9781792786242 Total Pages :32 pages Book Rating :4.7/5 (862 download)
Book Synopsis Investigation of Low-Reynolds-Number Rocket Nozzle Design Using Pns-Based Optimization Procedure by : National Aeronautics and Space Adm Nasa
Download or read book Investigation of Low-Reynolds-Number Rocket Nozzle Design Using Pns-Based Optimization Procedure written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2018-12-31 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: An optimization approach to rocket nozzle design, based on computational fluid dynamics (CFD) methodology, is investigated for low-Reynolds-number cases. This study is undertaken to determine the benefits of this approach over those of classical design processes such as Rao's method. A CFD-based optimization procedure, using the parabolized Navier-Stokes (PNS) equations, is used to design conical and contoured axisymmetric nozzles. The advantage of this procedure is that it accounts for viscosity during the design process; other processes make an approximated boundary-layer correction after an inviscid design is created. Results showed significant improvement in the nozzle thrust coefficient over that of the baseline case; however, the unusual nozzle design necessitates further investigation of the accuracy of the PNS equations for modeling expanding flows with thick laminar boundary layers. Hussaini, M. Moin and Korte, John J. Langley Research Center NASA-TM-110295, NAS 1.15:110295 RTOP 522-31-31-02...
Book Synopsis A Comparison of Methods for Predicting Performance of Low-thrust Rocket Nozzles by : John C. Tannehill
Download or read book A Comparison of Methods for Predicting Performance of Low-thrust Rocket Nozzles written by John C. Tannehill and published by . This book was released on 1967 with total page 156 pages. Available in PDF, EPUB and Kindle. Book excerpt:
