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An Evaluation Of Jet Simulation Parameters For Nozzle Afterbody Testing At Transonic Mach Numbers
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Book Synopsis An Evaluation of Jet Simulation Parameters for Nozzle Afterbody Testing at Transonic Mach Numbers by : William Lee Peters
Download or read book An Evaluation of Jet Simulation Parameters for Nozzle Afterbody Testing at Transonic Mach Numbers written by William Lee Peters and published by . This book was released on 1976 with total page 102 pages. Available in PDF, EPUB and Kindle. Book excerpt: The objective of this investigation was to evaluate various jet simulation parameters in an attempt to establish a method of matching hot jet interference with cold jet flows. Successful parameters were determined based on their ability to correlate integrated afterbody pressure drag, a measurement of aerodynamic interference, for jet flows of varying total temperature. Data used in this investigation were obtained from experiments conducted in the AEDC Propulsion Wind Tunnel (16T) with three different isolated nozzle/afterbody configurations at free-stream Mach numbers from 0.6 to 1.5. Gas temperature effects on pressure drag were acquired with a convergent nozzle utilizing an air/ethylene burner to produce gas temperatures from 540 to 3,300 R. In addition, the jet effects of varying internal nozzle geometry, specifically nozzle divergence half-angle and nozzle exit-to-throat area ratio, were investigated utilizing high-pressure air as the nozzle exhaust gas. Jet simulation parameters were evaluated for jet flows where nozzle exit-to-throat area ratio was varied from 1.0 to approximately 1.5 and where divergence half-angle was varied from 0 to 10 deg.
Book Synopsis An Evaluation of Jet Simulation Parameters for Nozzle Afterbody Testing at Transonic Mach Numbers by :
Download or read book An Evaluation of Jet Simulation Parameters for Nozzle Afterbody Testing at Transonic Mach Numbers written by and published by . This book was released on 1976 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: The objective of this investigation was to evaluate various jet simulation parameters in an attempt to establish a method of matching hot jet interference with cold jet flows. Successful parameters were determined based on their ability to correlate integrated afterbody pressure drag, a measurement of aerodynamic interference, for jet flows of varying total temperature. Data used in this investigation were obtained from experiments conducted in the AEDC Propulsion Wind Tunnel (16T) with three different isolated nozzle/afterbody configurations at free-stream Mach numbers from 0.6 to 1.5. Gas temperature effects on pressure drag were acquired with a convergent nozzle utilizing an air/ethylene burner to produce gas temperatures from 540 to 3,300 R. In addition, the jet effects of varying internal nozzle geometry, specifically nozzle divergence half-angle and nozzle exit-to-throat area ratio, were investigated utilizing high-pressure air as the nozzle exhaust gas. Jet simulation parameters were evaluated for jet flows where nozzle exit-to-throat area ratio was varied from 1.0 to approximately 1.5 and where divergence half-angle was varied from 0 to 10 deg.
Book Synopsis An Investigation of F-16 Nozzle-afterbody Forces at Transonic Mach Numbers with Emphasis on Support System Interference by : Earl A. Price (Jr.)
Download or read book An Investigation of F-16 Nozzle-afterbody Forces at Transonic Mach Numbers with Emphasis on Support System Interference written by Earl A. Price (Jr.) and published by . This book was released on 1979 with total page 416 pages. Available in PDF, EPUB and Kindle. Book excerpt: A comprehensive experimental program was conducted to provide nozzle-afterbody data with a minimum interference support system on a 1/9-scale F-16 model and to determine the interference induced on the afterbody-nozzle region by a sting, a wingtip, and a strut model support system. The investigation was conducted over the Mach number range from 0.6 to 1.5 and at angles of attack from 0 to 9 deg. Interference was evaluated by comparison of nozzle-afterboy axial and normal forces obtained from integrating pressure data. The results include parametric studies of the efects of various components of the wingtip support system (i.e., the support blade axial position, wingtip boom diameter, boom spacing, and boom-tip axial location). High-pressure air at ambient temperature was utilized for exhaust plume simulation. The results indicate that a sting support passing through the nozzle with the jet effects simulated by an annular jet appears to offer a minimum interference support system for the type of nozzle-afterbody test described in this report.
Book Synopsis An Evaluation of Nozzle Afterbody Code by : Frederick C. Guyton
Download or read book An Evaluation of Nozzle Afterbody Code written by Frederick C. Guyton and published by . This book was released on 1986 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Technical Memorandum written by and published by . This book was released on 1989 with total page 260 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Computation of Axisymmetric Separated Nozzle-afterbody Flow by : James L. Jacocks
Download or read book Computation of Axisymmetric Separated Nozzle-afterbody Flow written by James L. Jacocks and published by . This book was released on 1980 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: The development of a computer program for solving the compressible, axisymmetric, mass-averaged Navier-Stokes equations is described. The basic numerical algorithm is the MacCormack explicit predictor-corrector scheme. Turbulence modeling is accomplished using an algebraic, two-layer eddy viscosity model with a novel modification dependent on the streamwise gradient of vorticity. Comparisons of computed results with experimental data are presented for several nozzle-afterbody configurations with either or simulated plumes. (Author).
Book Synopsis Experimental Method for Correcting Nozzle Afterbody Drag for the Effects of Jet Temperature by : W. L. Peters
Download or read book Experimental Method for Correcting Nozzle Afterbody Drag for the Effects of Jet Temperature written by W. L. Peters and published by . This book was released on 1981 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt: The objective of this investigation was to isolate those parameters defined as jet mixing effects on afterbody drag in an effort to develop a method of correcting or simulating the effects of jet temperature in wind tunnel experiments. Data used in the investigation were obtained from experiments conducted in the AEDC Aerodynamic Wind Tunnel (1T) with a strut-mounted model at free-stream Mach numbers from 0.6 to 1.2. Integrated afterbody pressure drag coefficient data were acquired for three nozzle area ratios (1.0, 1.24, and 2.96) using various unheated jet exhaust gas compositions that allowed a variation in gas constant from 55 to 767 ft/lbf/lbm-deg R. Jet mixing effects on afterbody drag coefficient produced by varying jet gas constant and nozzle area ratio at nozzle design pressure ratio, and the drag effects resulting from variations in nozzle pressure ratio at certain overexpanded jet conditions were observed to be similar functions of mass flux ratio. A simple experimental method has been proposed to allow corrections of afterbody drag coefficient data obtained in the wind tunnel (using an ambient temperature air jet) for the effects of jet gas constant. By inference, a similar drag correction can be obtained for the combined effect of gas constant and temperature, assuming their product defines the effects on drag produced by variations in either property. (Author).
Book Synopsis Evaluation of Boattail Geometry and Exhaust Plume Temperature Effects on Nozzle Afterbody Drag at Transonic Mach Numbers by : L. L. Galigher
Download or read book Evaluation of Boattail Geometry and Exhaust Plume Temperature Effects on Nozzle Afterbody Drag at Transonic Mach Numbers written by L. L. Galigher and published by . This book was released on 1976 with total page 144 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental program was conducted to investigate the interaction effects which occur between the nozzle exhaust flow and the external flow field associated with isolated nozzle afterbody configurations at transonic Mach numbers. Pressure data were obtained from three afterbody geometries with boattail angles of 10, 15, and 25 deg at Mach numbers from 0.6 to 1.5 at zero angles of attack and sideslip. Cold (High-pressure air) and hot (Air/ethylene combustion) jet test techniques were used to simulate and duplicate, respectively, the nozzle exhaust flow for a sonic jet installation. Nozzle exhaust temperature was varied from 540 to approximately 2,900 R. The most significant results pertain to those effects on boattail pressure drag caused by exhaust plume temperature and flow asymmetry (Model support strut induced). The differences obtained in boattail pressure drag between the cold jet simulation and hot jet duplication results were significant at nozzle pressure ratios representative for turbofan and turbojet engines at subsonic Mach numbers. Adjusting the cold jet nozzle pressure ratio to correct for changes in the exhaust plume specific heat ratio with temperature did not account for the differences observed. Flow asymmetry effects were Mach number and nozzle pressure ratio dependent and increased in severity as the boattail angle was increased.
Book Synopsis A Parametric Investigation of the Annular Jet Concept for Obtaining Afterbody Drag Data at Transonic Mach Numbers by :
Download or read book A Parametric Investigation of the Annular Jet Concept for Obtaining Afterbody Drag Data at Transonic Mach Numbers written by and published by . This book was released on 1978 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: A parametric experimental program was conducted at free-stream Mach numbers of 0.6, 0.9, and 1.2 to investigate the plume simulation characteristics of annular jets. Plume simulation evaluation was based upon comparisons of afterbody pressure drag from integration of afterbody pressure measurements. Data were obtained on a 15-deg boattail afterbody attached to a strut-supported cylindrical centerbody. Geometric variables covered a range of sting-to-nozzle exit diameter ratios from 0 to 0.95 and nozzle area ratios from 1.0 to 1.5. High pressure air at ambient temperature was utilized for the exhaust gas. The results indicate that matching of the exhaust plume maximum diameter provides a reasonable afterbody drag correlation, accounting for effects of annular jet, nozzle exit-to-throat area ratio, and nozzle pressure ratio for conditions where drag follows the classical trend indicative of a plume shape dependence. Plume diameter correlation was not successful, for the pressure ratios of this investigation, for annular jet configurations having sting-to-nozzle exit diameter ratios of 0.95 at all Mach numbers and 0.866 at Mach number 1.2. There were no significant differences in the trends with angle of attack between the annular and conventional jet configurations over the angle-of-attack range from -2 to 6 deg. (Author).
Book Synopsis A Parametric Investigation of the Annular Jet Concept for Obtaining Afterbody Drag Data at Transonic Mach Numbers by : Earl A. Price (Jr.)
Download or read book A Parametric Investigation of the Annular Jet Concept for Obtaining Afterbody Drag Data at Transonic Mach Numbers written by Earl A. Price (Jr.) and published by . This book was released on 1978 with total page 182 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Investigation of F-16 Nozzle-Afterbody Forces at Transonic Mach Numbers with Emphasis on Support System Interference by : Earl A Price (Jr)
Download or read book An Investigation of F-16 Nozzle-Afterbody Forces at Transonic Mach Numbers with Emphasis on Support System Interference written by Earl A Price (Jr) and published by . This book was released on 1979 with total page 209 pages. Available in PDF, EPUB and Kindle. Book excerpt: A comprehensive experimental program was conducted to provide nozzle-afterbody data with a minimum interference support system on a 1/9-scale F-16 model and to determine the interference induced on the afterbody-nozzle region by a sting, a wingtip, and a strut model support system. The investigation was conducted over the Mach number range from 0.6 to 1.5 and at angles of attack from 0 to 9 deg. Interference was evaluated by comparison of nozzle-afterboy axial and normal forces obtained from integrating pressure data. The results include parametric studies of the efects of various components of the wingtip support system (i.e., the support blade axial position, wingtip boom diameter, boom spacing, and boom-tip axial location). High-pressure air at ambient temperature was utilized for exhaust plume simulation. The results indicate that a sting support passing through the nozzle with the jet effects simulated by an annular jet appears to offer a minimum interference support system for the type of nozzle-afterbody test described in this report.
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 1995 with total page 704 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Evaluation of Reynolds Number and Tunnel Wall Porosity Effects on Nozzle Afterbody Drag at Transonic Mach Numbers by : C. E. Robinson
Download or read book Evaluation of Reynolds Number and Tunnel Wall Porosity Effects on Nozzle Afterbody Drag at Transonic Mach Numbers written by C. E. Robinson and published by . This book was released on 1976 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was conducted to study the effects of Reynolds number variation on isolated nozzle afterbody performance. A strut-mounted cone-cylinder model with three separate afterbody configurations for Aerospace Research and Development (AGARD) was used for this investigation. This program was conducted in two phases distinguished by the model size and the wind tunnels used to obtain the experimental results. The effect of tunnel wall porosity on nozzle afterbody (NAB) performance was investigated.
Book Synopsis Exhaust Plume Temperature Effects on Nozzle Afterbody Performance Over the Transonic Mach Number Range by : C. E. Robinson
Download or read book Exhaust Plume Temperature Effects on Nozzle Afterbody Performance Over the Transonic Mach Number Range written by C. E. Robinson and published by . This book was released on 1974 with total page 98 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results of an experimental and analytical research investigation on nozzle/afterbody drag are presented. Experimental afterbody (and boattail) drag coefficients and pressure distributions are discussed for an isolated, strut-mounted nozzle/afterbody model for the Mach number range from 0.6 to 1.5. Some data are also given for free-stream unit Reynolds numbers from one million to approximately four million per foot. The experimental data were obtained for the basic model with an air-cooled and a water-cooled Ethylene/air combustor to provide hot-jet duplication as well as cold-jet simulation. The temperature of the nozzle exhaust gas was varied from 530R (burner-off) to approximately 2500R for several nozzle pressure ratios from jet-off to those corresponding to a moderately under-expanded exhaust plum. The initial series of experiments was conducted with the air-cooled combustors, and the effect of jet temperature on afterbody drag was somewhat masked by the effects of the secondary airflow from the cooling air. The general trend, however, shows a decreasing afterbody drag with increasing exhaust gas temperature and with decreasing secondary airflow at a fixed nozzle pressure ratio. (Modified author abstract).
Book Synopsis Effect of Jet Velocity and Axial Location of Nozzle Exit on the Performance of a Twin-jet Afterbody Model at Mach Numbers Up to 2.2 by : Bobbly Lee Berrier
Download or read book Effect of Jet Velocity and Axial Location of Nozzle Exit on the Performance of a Twin-jet Afterbody Model at Mach Numbers Up to 2.2 written by Bobbly Lee Berrier and published by . This book was released on 1969 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Evaluation of Boattail Geometry and Exhaust Plume Temperature Effects on Nozzle Afterbody Drag at Transonic Mach Numbers by : L. L. Galigher
Download or read book Evaluation of Boattail Geometry and Exhaust Plume Temperature Effects on Nozzle Afterbody Drag at Transonic Mach Numbers written by L. L. Galigher and published by . This book was released on 1976 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental program was conducted to investigate the interaction effects which occur between the nozzle exhaust flow and the external flow field associated with isolated nozzle afterbody configurations at transonic Mach numbers. Pressure data were obtained from three afterbody geometries with boattail angles of 10, 15, and 25 deg at Mach numbers from 0.6 to 1.5 at zero angles of attack and sideslip. Cold (High-pressure air) and hot (Air/ethylene combustion) jet test techniques were used to simulate and duplicate, respectively, the nozzle exhaust flow for a sonic jet installation. Nozzle exhaust temperature was varied from 540 to approximately 2,900 R. The most significant results pertain to those effects on boattail pressure drag caused by exhaust plume temperature and flow asymmetry (Model support strut induced). The differences obtained in boattail pressure drag between the cold jet simulation and hot jet duplication results were significant at nozzle pressure ratios representative for turbofan and turbojet engines at subsonic Mach numbers. Adjusting the cold jet nozzle pressure ratio to correct for changes in the exhaust plume specific heat ratio with temperature did not account for the differences observed. Flow asymmetry effects were Mach number and nozzle pressure ratio dependent and increased in severity as the boattail angle was increased.
Book Synopsis A Parametric Investigation of the Annular Jet Concept for Obtaining Afterbody Drag Data at Transonic Mach Numbers by :
Download or read book A Parametric Investigation of the Annular Jet Concept for Obtaining Afterbody Drag Data at Transonic Mach Numbers written by and published by . This book was released on 1978 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: A parametric experimental program was conducted at free-stream Mach numbers of 0.6, 0.9, and 1.2 to investigate the plume simulation characteristics of annular jets. Plume simulation evaluation was based upon comparisons of afterbody pressure drag from integration of afterbody pressure measurements. Data were obtained on a 15-deg boattail afterbody attached to a strut-supported cylindrical centerbody. Geometric variables covered a range of sting-to-nozzle exit diameter ratios from 0 to 0.95 and nozzle area ratios from 1.0 to 1.5. High pressure air at ambient temperature was utilized for the exhaust gas. The results indicate that matching of the exhaust plume maximum diameter provides a reasonable afterbody drag correlation, accounting for effects of annular jet, nozzle exit-to-throat area ratio, and nozzle pressure ratio for conditions where drag follows the classical trend indicative of a plume shape dependence. Plume diameter correlation was not successful, for the pressure ratios of this investigation, for annular jet configurations having sting-to-nozzle exit diameter ratios of 0.95 at all Mach numbers and 0.866 at Mach number 1.2. There were no significant differences in the trends with angle of attack between the annular and conventional jet configurations over the angle-of-attack range from -2 to 6 deg. (Author).
