An Evaluation of Nozzle Afterbody Code PDF Download
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Author: Frederick C. Guyton
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 68
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Author: Frederick C. Guyton
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 68
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Author: W. L. Peters
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 50
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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).
Author: James L. Jacocks
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 36
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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).
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 260
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Author: L. L. Galigher
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 144
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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.
Author: Earl A. Price (Jr.)
Publisher:
ISBN:
Category : Drag (Aerodynamics)
Languages : en
Pages : 182
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 704
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Author: C. E. Robinson
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 38
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Book Description
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.
Author: W. L. Peters
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 120
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Book Description
The objective of this investigation was to evaluate the effects of individual jet exhaust properties on afterbody drag coefficient and to determine whether these properties affect drag by primarily altering the jet plume shape and/or jet entrainment. A large reduction in afterbody drag coefficient was observed with a decrease in the specific heat ratio at most underexpanded nozzle flow conditions. Regardless of free-stream Mach number of afterbody external configuration, an increase in the gas constant produced a consistent reduction in afterbody drag coefficient that was not a function of nozzle pressure ratio. The effects of gas constant increased for separated afterbody configurations and at transonic free-stream Mach numbers. From analysis of the experimental data, it was concluded that the effects of gas constant and specific heat ratio were, to a large extent separate, that the gas constant affected afterbody drag solely through the extrainment or mixing process, and that the specific heat ratio affected the drag primarily through determination of the inviscid jet plume shape.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 528
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