An Evaluation Of Jet Simulation Parameters For Nozzle Afterbody Testing At Transonic Mach Numbers
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An Evaluation Of Jet Simulation Parameters For Nozzle Afterbody Testing At Transonic Mach Numbers
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Author : William Lee Peters
language : en
Publisher:
Release Date : 1976
An Evaluation Of Jet Simulation Parameters For Nozzle Afterbody Testing At Transonic Mach Numbers written by William Lee Peters and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1976 with Airplanes categories.
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.
An Evaluation Of Jet Simulation Parameters For Nozzle Afterbody Testing At Transonic Mach Numbers
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Author :
language : en
Publisher:
Release Date : 1976
An Evaluation Of Jet Simulation Parameters For Nozzle Afterbody Testing At Transonic Mach Numbers written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1976 with categories.
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.
An Investigation Of F 16 Nozzle Afterbody Forces At Transonic Mach Numbers With Emphasis On Support System Interference
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Author : Earl A. Price (Jr.)
language : en
Publisher:
Release Date : 1979
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 has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1979 with Aerodynamics, Transonic categories.
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.
An Evaluation Of Nozzle Afterbody Code
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Author : Frederick C. Guyton
language : en
Publisher:
Release Date : 1986
An Evaluation Of Nozzle Afterbody Code written by Frederick C. Guyton and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1986 with Boundary layer categories.
Evaluation Of Boattail Geometry And Exhaust Plume Temperature Effects On Nozzle Afterbody Drag At Transonic Mach Numbers
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Author : L. L. Galigher
language : en
Publisher:
Release Date : 1976
Evaluation Of Boattail Geometry And Exhaust Plume Temperature Effects On Nozzle Afterbody Drag At Transonic Mach Numbers written by L. L. Galigher and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1976 with Aerodynamics, Transonic categories.
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.
An Investigation Of F 16 Nozzle Afterbody Forces At Transonic Mach Numbers With Emphasis On Support System Interference
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Author :
language : en
Publisher:
Release Date : 1979
An Investigation Of F 16 Nozzle Afterbody Forces At Transonic Mach Numbers With Emphasis On Support System Interference written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1979 with categories.
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.
Computation Of Axisymmetric Separated Nozzle Afterbody Flow
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Author : James L. Jacocks
language : en
Publisher:
Release Date : 1980
Computation Of Axisymmetric Separated Nozzle Afterbody Flow written by James L. Jacocks and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1980 with Airplanes categories.
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).
Nasa Technical Memorandum
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Author :
language : en
Publisher:
Release Date : 1989
Nasa Technical Memorandum written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1989 with Aeronautics categories.
Experimental Method For Correcting Nozzle Afterbody Drag For The Effects Of Jet Temperature
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Author : W. L. Peters
language : en
Publisher:
Release Date : 1981
Experimental Method For Correcting Nozzle Afterbody Drag For The Effects Of Jet Temperature written by W. L. Peters and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1981 with Airplanes categories.
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).
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
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Author : Bobbly Lee Berrier
language : en
Publisher:
Release Date : 1969
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 has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1969 with Drag (Aerodynamics) categories.
