NDLI: Theoretical evaluation of a v/stol fighter model utilizing the pan air code

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Theoretical evaluation of a v/stol fighter model utilizing the pan air code

Content Provider	NASA Technical Reports Server (NTRS)
Author	Bhateley, I. C. Howell, G. A.
Copyright Year	1982
Description	The PAN AIR computer code was investigated as a tool for predicting closely coupled aerodynamic and propulsive flowfields of arbitrary configurations. The NASA/Ames V/STOL fighter model, a configuration of complex geometry, was analyzed with the PAN AIR code. A successful solution for this configuration was obtained when the nozzle exit was treated as an impermeable surface and no wakes were included around the nozzle exit. When separated flow was simulated from the end of the nacelle, requiring the use of wake networks emanating from the nozzle exit, a number of problems were encountered. A circular body nacelle model was used to investigate various techniques for simulating the exhaust plume in PAN AIR. Several approaches were tested and eliminated because they could not correctly simulate the interference effects. Only one plume modeling technique gave good results. A PAN AIR computation that used a plume shape and inflow velocities obtained from the Navier-Stokes solution for the plume produced results for the effects of power that compared well with experimental data.
File Size	2927822
Page Count	100
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19830009242
Archival Resource Key	ark:/13960/t3421st25
Language	English
Publisher Date	1982-09-01
Access Restriction	Open
Subject Keyword	Aerodynamics Navier-stokes Equation V/stol Aircraft Aerodynamic Configurations Flow Distribution Nacelles Computerized Simulation Plumes Computer Programs Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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