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General purpose computer program for interacting supersonic configurations. User's manualThe input data required to execute the computer program ISCON are described. The program generates a numerical procedure for the determination of unsteady aerodynamic forces on arbitrarily interacting wings and tails in supersonic flow. A velocity potential gradient method is used. Constant Mach number is assumed throughout the flow field. Lifting surfaces are represented by trapezoidal elements which can be generated automatically by the program. The wake field is represented by rectangular strip elements. The formulation is reviewed as well as input overview and input format. Instruction on how to use ISCON, a sample problem, and the restart feature are discussed. Program size limitations, computer program flow, and error messages are also included along with a description of the SS31 program used to compute the coefficients of surface spline.
Document ID
19790009627
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Crill, W.
(Textron Bell Aerospace Co. Buffalo, NY, United States)
Dale, B.
(Textron Bell Aerospace Co. Buffalo, NY, United States)
Date Acquired
September 3, 2013
Publication Date
January 1, 1977
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-145128
Accession Number
79N17798
Funding Number(s)
CONTRACT_GRANT: NAS1-13986
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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