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Analysis Of The Axisymmetric Base Pressure And Base Temperature Problem With Supersonic Interacting Freestream Nozzle Flows Based On The Flow Model Of Korst Et Al Part Iii A Computer Program And Representative Results For Cylindrical Boattailed Or Flared Afterbodies
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Book Synopsis Analysis of the Axisymmetric Base-Pressure and Base-Temperature Problem with Supersonic Interacting Freestream-Nozzle Flows Based on the Flow Model of Korst, Et Al. Part III. A Computer Program and Representative Results for Cylindrical, Boattailed, Or Flared Afterbodies by : A. L. Addy
Download or read book Analysis of the Axisymmetric Base-Pressure and Base-Temperature Problem with Supersonic Interacting Freestream-Nozzle Flows Based on the Flow Model of Korst, Et Al. Part III. A Computer Program and Representative Results for Cylindrical, Boattailed, Or Flared Afterbodies written by A. L. Addy and published by . This book was released on 1970 with total page 144 pages. Available in PDF, EPUB and Kindle. Book excerpt: The computer program presented and discussed in Part 1 of this report for analyzing the axisymmetric base-pressure and base-temperature problem with interacting supersonic free-stream and propulsive-nozzle flows was improved and generalized to include the analysis of an afterbody upstream of the base region. The afterbody geometries considered are: cylindrical, conical, parabolic, and tangent-ogive boattails and conical flares. The F0RTRAN IV computer-program listing, as well as detailed information on program development, organization, and usage, are included. Theoretical afterbody and base-pressure results are presented for parametric variations in afterbody geometry and flow variables. In addition, a limited comparison between theoretical and experimental conical- afterbody and base-pressure data is made.
Download or read book Paper written by and published by . This book was released on 1972 with total page 798 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Journal of Engineering for Industry by :
Download or read book Journal of Engineering for Industry written by and published by . This book was released on 1996 with total page 1228 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book AIAA 84-0301 - AIAA 84-0350 written by and published by . This book was released on 1984 with total page 472 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Proceedings written by and published by . This book was released on 1973 with total page 1378 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aerodynamic Drag written by and published by . This book was released on 1973 with total page 372 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :University of Illinois at Urbana-Champaign. Office of Engineering Publications Publisher : ISBN 13 : Total Pages :222 pages Book Rating :4.:/5 (31 download)
Book Synopsis The Summary of Engineering Research by : University of Illinois at Urbana-Champaign. Office of Engineering Publications
Download or read book The Summary of Engineering Research written by University of Illinois at Urbana-Champaign. Office of Engineering Publications and published by . This book was released on 1971 with total page 222 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Theory for Base Pressures in Transonic and Supersonic Flow by : Helmut Hans Korst
Download or read book A Theory for Base Pressures in Transonic and Supersonic Flow written by Helmut Hans Korst and published by . This book was released on 1962 with total page 146 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Application of the Chapman-Korst Theory to Supersonic Nozzle-afterbody Flows by : R. C. Bauer
Download or read book An Application of the Chapman-Korst Theory to Supersonic Nozzle-afterbody Flows written by R. C. Bauer and published by . This book was released on 1977 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt: A Chapman-Korst-type analysis has been developed for estimating the bulk base flow properties of nozzle-afterbody configurations operating at supersonic speeds. The analysis includes the effects of both initial boundary layers, dissimilar thermodynamic properties of both streams, and a third base bleed gas. The inviscid portions of the jet and external flow are computed by the method of characteristics. The turbulent mixing analysis uses the turbulent kinetic energy method to determine the coefficient in a Prandtl-type eddy viscosity model. The empirical coefficients in the turbulent kinetic energy formulation are those developed for the turbulent mixing of jet flows. A new analytical model of the recompression process has been developed that eliminates the need for an empirical recompression factor to determine the stagnating streamline. The analysis is evaluated by comparing with experimental data for Mach 2.0 flow over a two-dimensional blunt base with hydrogen bleed, a two-dimensional backward-facing step and a hot and a cold rocket nozzle-afterbody configuration. Usually the theoretical base pressure is greater than experimental base pressure, indicating the mixing rate is too small. However, the recompression analysis predicts reasonable values of the recompression factor. (Author).
Book Synopsis An Experimental Investigation of the Supersonic Axisymmetric Base Flow Behind a Cylindrical Afterbody by : Jeff Lee Herrin
Download or read book An Experimental Investigation of the Supersonic Axisymmetric Base Flow Behind a Cylindrical Afterbody written by Jeff Lee Herrin and published by . This book was released on 1991 with total page 208 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Application of the Chapman-Korst Theory to Supersonic Nozzle-Afterbody Flows by :
Download or read book An Application of the Chapman-Korst Theory to Supersonic Nozzle-Afterbody Flows written by and published by . This book was released on 1977 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: A Chapman-Korst-type analysis has been developed for estimating the bulk base flow properties of nozzle-afterbody configurations operating at supersonic speeds. The analysis includes the effects of both initial boundary layers, dissimilar thermodynamic properties of both streams, and a third base bleed gas. The inviscid portions of the jet and external flow are computed by the method of characteristics. The turbulent mixing analysis uses the turbulent kinetic energy method to determine the coefficient in a Prandtl-type eddy viscosity model. The empirical coefficients in the turbulent kinetic energy formulation are those developed for the turbulent mixing of jet flows. A new analytical model of the recompression process has been developed that eliminates the need for an empirical recompression factor to determine the stagnating streamline. The analysis is evaluated by comparing with experimental data for Mach 2.0 flow over a two-dimensional blunt base with hydrogen bleed, a two-dimensional backward-facing step and a hot and a cold rocket nozzle-afterbody configuration. Usually the theoretical base pressure is greater than experimental base pressure, indicating the mixing rate is too small. However, the recompression analysis predicts reasonable values of the recompression factor. (Author).
Book Synopsis Analytical Nodel of Supersonic, Turbulent, Near-wake Flows by : C. E. Peters
Download or read book Analytical Nodel of Supersonic, Turbulent, Near-wake Flows written by C. E. Peters and published by . This book was released on 1976 with total page 80 pages. Available in PDF, EPUB and Kindle. Book excerpt: An analytical model for planar and axisymmetric, supersonic, turbulent, near-wake flows is presented. The viscous region behind the blunt base is described by the integral form of the boundary-layer equations, and the inviscid outer-flow region, including the remnant of the initial turbulent boundary layer, is computed with the rotational method of characteristics. The solution of the two regions is fully coupled. The saddle-point singularity, similar to the Crocco-Lees critical point, occurs downstream of the rear stagnation point. The base pressure is obtained by iteration of the initial conditions until the flow-field solution will pass through the singularity. Base bleed of a gas different from the outer-stream gas is included in the formulation, and provision is made to treat equilibrium chemical reactions in the viscous wake. However, an unresolved problem has been encountered in the solution of the species conservation equations. Therefore, results for only single gas flows are presented. The analytical model is shown to adequately predict the effect of free-stream Mach number and initial boundary layer on the planar base pressure. In addition, the planar flow-field structure is well predicted. Axisymmetric base pressure and flow-field structure are reasonably well predicted for free-stream Mach numbers greater than 2.0, but the turbulent transport model used yields only fair results for Mach numbers less than 1.7. The effect of base bleed on the axisymmetric base pressure is well predicted. (Author).
Book Synopsis Base Pressure Studies in Rarefied Supersonic Flows by : Lawrence Lewis Kavanau
Download or read book Base Pressure Studies in Rarefied Supersonic Flows written by Lawrence Lewis Kavanau and published by . This book was released on 1955 with total page 258 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Experimental Investigation of Supersonic Axisymmetric Base Flows Including the Effects of Afterbody Boattailing by : Jeff Lee Herrin
Download or read book An Experimental Investigation of Supersonic Axisymmetric Base Flows Including the Effects of Afterbody Boattailing written by Jeff Lee Herrin and published by . This book was released on 1993 with total page 476 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Jet Effects on Annular Base Pressure and Temperature in a Supersonic Stream by : Milton A. Beheim
Download or read book Jet Effects on Annular Base Pressure and Temperature in a Supersonic Stream written by Milton A. Beheim and published by . This book was released on 1962 with total page 112 pages. Available in PDF, EPUB and Kindle. Book excerpt: The theoretical and experimental investigation was conducted with single jet configurations at free-stream Mach numbers of 2.0 and 1.6. Theoretical base-pressure ratios were generally less than experimental values but were in closer agreement for the short-nozzle designs than for the full-length isentropic nozzles. In general the predicted base-temperature ratios were greater than experimental values, and this deviation decreased with increasing ratio of jet total to base static pressure. This deviation was less at Mach 1.6 than at 2.0 and was less for high-area-ratio nozzles than for low-area-ratio designs. The effect of base bleed on base pressure could be predicted with good accuracy at low bleed-flow rates.
Book Synopsis A Study of the Effects of Boundary Layer on Axisymmetric Jet-On Base Pressure in Transonic and Supersonic Flows by : Alva L. Addy
Download or read book A Study of the Effects of Boundary Layer on Axisymmetric Jet-On Base Pressure in Transonic and Supersonic Flows written by Alva L. Addy and published by . This book was released on 1972 with total page 13 pages. Available in PDF, EPUB and Kindle. Book excerpt: The onset and effects of plume-induced boundary-layer separation on the afterbody during powered supersonic flight were investigated. Plume-induced separation occurs for configurations designed for overall drag reduction since boattailing, base bleed, nozzle exit angle, and nozzle extension tend to increase significantly the base pressure. However, each configuration and set of operating conditions must be studied. The purpose of this report is to present only a brief summary of the investigation and to reference the publications which contain the details.
Book Synopsis Hypersonic Flow Theory: Inviscid flows by : Wallace Dean Hayes
Download or read book Hypersonic Flow Theory: Inviscid flows written by Wallace Dean Hayes and published by . This book was released on 1966 with total page 632 pages. Available in PDF, EPUB and Kindle. Book excerpt:
