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An Evaluation of Nozzle Afterbody Code

Author: Frederick C. Guyton
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 68

Book Description

An Evaluation of Nozzle Afterbody Code

Author: Frederick C. Guyton
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 68

Book Description

An Evaluation of Nozzle Afterbody Code - AR02P.

Author: Frederick C. Guyton
Publisher:
ISBN:
Category :
Languages : en
Pages : 34

Book Description
A project was undertaken to develop a computational fluid dynamics (CFD) code for use in nozzle afterbody analysis. Objectives were to create a three-dimensional code capable of calculating afterbody flows with accuracy quantitatively close to the Navier-Stokes solutions, but which would use significantly fewer computer resources. The resulting program coupled an inverse boundary-layer routine with an Euler code and incorporated a jet plume. Calculations were made for the axisymmetric AGARD 15-deg boattail afterbody with variations in nozzle pressure ratio for Mach numbers 0.6 and 0.9, and compared with experimental results. The code predicted drag changes with NPR which showed the proper variations, but the code did not provide the accuracy required for typical nozzle afterbody analysis. (NPR = Nozzle total pressure to free stream static pressure ratio.).

An Evaluation of Nozzle Afterbody Code

Author: Frederick C. Guyton
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 0

Book Description

Scientific and Technical Aerospace Reports

Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 500

Book Description

Evaluation of Reynolds Number and Tunnel Wall Porosity Effects on Nozzle Afterbody Drag at Transonic Mach Numbers

Author: C. E. Robinson
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 38

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.