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Wind Tunnel Model Design For The Study Of Plume Effects On Sonic Boom For Isolated Exhaust Nozzles
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Book Synopsis Wind Tunnel Model Design for the Study of Plume Effects on Sonic Boom for Isolated Exhaust Nozzles by : Raymond S. Castner
Download or read book Wind Tunnel Model Design for the Study of Plume Effects on Sonic Boom for Isolated Exhaust Nozzles written by Raymond S. Castner and published by . This book was released on 2010 with total page 10 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Exhaust Nozzle Plume Effects on Sonic Boom Test Results for Isolated Nozzles by : Raymond S. Castner
Download or read book Exhaust Nozzle Plume Effects on Sonic Boom Test Results for Isolated Nozzles written by Raymond S. Castner and published by . This book was released on 2011 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Adm Nasa Publisher :Independently Published ISBN 13 :9781794059351 Total Pages :48 pages Book Rating :4.0/5 (593 download)
Book Synopsis Cfd Analysis of Nozzle Jet Plume Effects on Sonic Boom Signature by : National Aeronautics and Space Adm Nasa
Download or read book Cfd Analysis of Nozzle Jet Plume Effects on Sonic Boom Signature written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2019-01-14 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt: A computational fluid dynamics study is conducted to examine nozzle exhaust jet plume effects on the Sonic boom signature of a supersonic aircraft. A simplified axisymmetric nozzle geometry, representative of the nozzle on the NASA Dryden NF-15B Lift and Nozzle Change Effects on Tail Shock research airplane, is considered. The computational fluid dynamics code is validated using available wind-tunnel sonic boom experimental data. The effects of grid size, spatial order of accuracy. grid type, and flow viscosity on the accuracy of the predicted sonic boom pressure signature are quantified. Grid lines parallel to the Mach wave direction are found to give the best results. Second-order accurate upwind methods are required as a minimum for accurate sonic boom simulations. The highly underexpanded nozzle flow is found to provide significantly more reduction in the tail shock strength in the sonic boom N-wave pressure signature than perfectly expanded and overexpanded nozzle flows. A tail shock train in the sonic boom signature is observed for the highly underexpanded nozzle flow. Axisymmetric computational fluid dynamics simulations show the flow physics inside the F-15 nozzle to be nonisentropic and complex. NASA/TM-2009-214650, AIAA Paper 2009-1054, H-2923, DFRC-938 Bui, Trong T. Armstrong Flight Research Center
Book Synopsis 2023 Asia-Pacific International Symposium on Aerospace Technology (APISAT 2023) Proceedings by : Song Fu
Download or read book 2023 Asia-Pacific International Symposium on Aerospace Technology (APISAT 2023) Proceedings written by Song Fu and published by Springer Nature. This book was released on with total page 1991 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1986 with total page 1162 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aeronautical Engineering written by and published by . This book was released on 1971 with total page 580 pages. Available in PDF, EPUB and Kindle. Book excerpt: A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA)
Download or read book NASA SP. written by and published by . This book was released on 1991 with total page 384 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis NASA Scientific and Technical Publications by :
Download or read book NASA Scientific and Technical Publications written by and published by . This book was released on 1993 with total page 134 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis NASA Scientific and Technical Publications: A Catalog of Special Publications, Reference Publications, Conference Publications, and Technical Papers, 1991-1992 by :
Download or read book NASA Scientific and Technical Publications: A Catalog of Special Publications, Reference Publications, Conference Publications, and Technical Papers, 1991-1992 written by and published by . This book was released on 1993 with total page 122 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wind Tunnel Model Study of the Hot Exhaust Plume from the Compressor Research Facility at Wright-Patterson Air Force Base, Ohio by : Gary R. Ludwig
Download or read book Wind Tunnel Model Study of the Hot Exhaust Plume from the Compressor Research Facility at Wright-Patterson Air Force Base, Ohio written by Gary R. Ludwig and published by . This book was released on 1977 with total page 155 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report presents the results of a wind tunnel model study to determine temperatures at various locations generated by the hot exhaust air from the Compressor Research Facility (CRF) which is being built at Wright-Patterson Air Force Base, Ohio. The study was designed to provide data at the inlet to the CRF and at other nearby locations where pedestrians, building ventilation systems, and vegetation might be affected. The test program, which was conducted in the Calspan Atmospheric Simulation Facility, included flow visualization studies and quantitative concentration measurements of a tracer gas from which full-scale temperatures could be calculated. The concentration measurements were performed for a number of wind speeds at each of twelve different wind directions. Two exhaust flows and two exhaust stack configurations were studied. (Author).
Book Synopsis Full Scale Subsonic Wind Tunnel Requirements and Design Studies by : Mark W. Kelly
Download or read book Full Scale Subsonic Wind Tunnel Requirements and Design Studies written by Mark W. Kelly and published by . This book was released on 1972 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Model Study of the Exhaust Flow Noise of the Proposed AEDC High Reynolds Number Tunnel by : J. E. Robertson
Download or read book Model Study of the Exhaust Flow Noise of the Proposed AEDC High Reynolds Number Tunnel written by J. E. Robertson and published by . This book was released on 1971 with total page 112 pages. Available in PDF, EPUB and Kindle. Book excerpt: A study to evaluate the exhaust noise environment of a proposed high Reynolds number tunnel (HIRT) has been conducted. During an earlier phase of this study, prediction of the noise environment resulting from both the starting transient and steady-stage operation of the facility was performed. Also, a model test program was specified to experimentally evaluate the exhaust flow noise. The results of the model test program and new predictions of the full-scale HIRT exhaust noise, based on the model data, are the subjects of the report. (Author).
Book Synopsis Wind Tunnel/flight Data Correlation (u). by : James A. Behal
Download or read book Wind Tunnel/flight Data Correlation (u). written by James A. Behal and published by . This book was released on 1971 with total page 692 pages. Available in PDF, EPUB and Kindle. Book excerpt: A program was conducted to obtain data, both steady state and dynamic, from wind tunnel models and full scale flight tests of the RA-5C aircraft. Data were acquired on 0.228 and 0. 125 scale RA-5C inlet models and on a fully instrumented flight test RA-5C aircraft. Interim data reports presenting the data acquired during each test have been published. These data were utilized in this report to develop scaling techniques for correlating small scale model wind tunnel data with full scale flight data. Data presented include duct steady state operating characteristics and pressure distributions in the inlet and at the engine face. Dynamic data are presented in the form of engine face turbulence contour plots, radial turbulence distributions and selected spectral data functions. Data are presented for variations of angle of attack, angle of yaw, Reynolds number, ramp angle, secondary flow rates and inlet diverter width. Brief descriptions of the model and test methods are also presented.
Book Synopsis Quieting the Boom by : Lawrence R. Benson
Download or read book Quieting the Boom written by Lawrence R. Benson and published by . This book was released on 2013 with total page 388 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Electric Resistance Air Heater for a Low Density Wind Tunnel by : Velvin Richard Watson
Download or read book An Electric Resistance Air Heater for a Low Density Wind Tunnel written by Velvin Richard Watson and published by . This book was released on 1961 with total page 156 pages. Available in PDF, EPUB and Kindle. Book excerpt: An electric resistance air heater for wind tunnel 4 of the Aeronautical Sciences Laboratory at the University of California was constructed and proven satisfactory in performance tests. The heater increased the range of stagnation temperature to 1600 F, thereby increasing the experimental range of test conditions of the wind tunnel to include higher Mach numbers, deeper penetration of the slip flow region, and temperatures more nearly simulating free flight conditions.
Book Synopsis Effect of Design Changes on Aerodynamic and Acoustic Performance of Translating-centerbody Sonic Inlets by : Brent A. Miller
Download or read book Effect of Design Changes on Aerodynamic and Acoustic Performance of Translating-centerbody Sonic Inlets written by Brent A. Miller and published by . This book was released on 1978 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was conducted to determine the effect of design changes on the aerodynamic and acoustic performance of translating centerbody sonic inlets. Scale model inlets were tested in the Lewis Research Center's V/STOL wind tunnel. The effects of centerbody position, entry lip contraction ratio, diffuser length, and diffuser area ratio on inlet total pressure recovery, distortion, and noise suppression were investigated at static conditions and at forward velocity and angle of attack. With the centerbody in the takeoff position (retracted), good aerodynamic and acoustic performance was attained at static conditions and at forward velocity. At 0 deg incidence angle with a sound pressure level reduction of 20 dB, the total pressure recovery was 0.986. Pressure recovery at 50 deg was 0.981. With the centerbody in the approach position (extended), diffuser flow separation occurred at an incidence angle of approximately 20 deg. However, good performance was attained at lower angles. With the centerbody in the takeoff position the ability of the inlet to tolerate high incidence angles was improved by increasing the lip contraction ratio. However, at static conditions with the centerbody in the approach position, an optimum lip contraction ratio appears to exist, with both thinner and thicker lips yielding reduced performance.
Book Synopsis Cold Flow Testing of a Modified Subscale Model Exhaust System for a Space Based Laser by : David B. Jarrett
Download or read book Cold Flow Testing of a Modified Subscale Model Exhaust System for a Space Based Laser written by David B. Jarrett and published by . This book was released on 2004-06-01 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt: The aim of this research was a continued study of gas-dynamic phenomena that occurred in a set of stacked nozzles as reported by Captains Ian Bautista in 2003 and Scott Bergren in 2002. The arrangement of the stacked nozzles was a modified version of a 1/5th scale-model of one quadrant of the conceptual Space Based Laser Integrated Flight Experiment (SBL IFX) gas dynamic laser. Rather than cylindrical rings of nozzles, the stacked nozzles were flat and able to be rotated about a vector normal to the nozzle exits. This set of stacked flat nozzles was installed on a blow-down/vacuum wind tunnel, which in addition to the nozzles, consisted of a stilling chamber, centerbody, supersonic diffuser, and transition structure to join the vacuum and test sections. The goals of this research were two fold; first, modify the original scale-model of the stacked cylindrical rings of nozzles so schlieren photography could be used to visualize an average flow field across the nozzles. Secondly, using the schlieren photographs, in conjunction with pressure data, observe the interactions between the individual nozzles. Results have shown that the modified nozzle array produces a vastly complex flow field as well as a highly supersonic flow r gime, with Mach numbers that reach as high as 5.6.
