NDLI: Unsteady transonic flow calculations for wing-fuselage configurations

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Unsteady transonic flow calculations for wing-fuselage configurations

Content Provider	NASA Technical Reports Server (NTRS)
Author	Batina, J. T.
Copyright Year	1986
Description	Unsteady transonic flow calculations are presented for wing-fuselage configurations. Calculations are performed by extending the XTRAN3S unsteady transonic small-disturbance code to allow the treatment of a fuselage. Details of the XTRAN3S fuselage modeling are discussed in the context of the small-disturbance equation. Transonic calculations are presented for three wing-fuselage configurations with leading edge sweep angles ranging from 0 deg to 46.76 deg. Simple bending and torsion modal oscillations of the wing are calculated. Sectional lift and moment coefficients for the wing-alone and wing-fuselage cases are compared and the effects of fuselage aerodynamic interference on the unsteady wing loading are revealed. Tabulated generalized aerodynamic forces used in flutter analyses, indicate small changes in the real in-phase component and as much as a 30% change in the imaginary component when the fuselage is included in the calculation. These changes result in a 2 to 5% increase in total magnitude and a several degree increase in phase.
File Size	848418
Page Count	17
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19860015186
Archival Resource Key	ark:/13960/t27992700
Language	English
Publisher Date	1986-03-01
Access Restriction	Open
Subject Keyword	Aerodynamics Transonic Flow Body-wing Configurations Computational Fluid Dynamics Finite Difference Theory Aerodynamic Interference Fuselages Unsteady Flow Computational Grids Aeroelasticity Leading Edge Sweep Aerodynamic Loads Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Article

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