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Calculations of the pressure distribution on axisymmetric boattails including effects of viscous interactions and exhaust jets in subsonic flowA method of calculating the pressure distributions on boattails is proposed. This method accounts for viscous effects including the presence of a separated region for base flows by combining an inviscid analysis with a boundary layer analysis in an iterative calculation. Details of the reversed flow region are not considered. Some preliminary results have been obtained for boattails at subsonic free stream Mach number with turbulent boundary layers separating at the boattail base. In some cases convergence could not be obtained using the present computer program. It is possible, in principle, to extend this method to the calculation of boattail flows with pressure gradient induced separation on the boattail.
Document ID
19740024298
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Rom, J. (Technical - Israel Inst. of Tech. Haifa, United States)
Bober, L. J. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
September 1, 1974
Subject Category
Aerodynamics
Report/Patent Number
E-7811
NASA-TM-X-3109
Accession Number
74N32411
Funding Number(s)
PROJECT: RTOP 501-24
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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