NDLI: Computer program for definition of transonic axial-flow compressor blade rows. [computer program for fabrication and aeroelastic analysis

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Computer program for definition of transonic axial-flow compressor blade rows. [computer program for fabrication and aeroelastic analysis

Content Provider	NASA Technical Reports Server (NTRS)
Author	Crouse, J. E.
Copyright Year	1974
Description	A method is presented for designing axial-flow compressor blading from blade elements defined on cones which pass through the blade-edge streamline locations. Each blade-element centerline is composed of two segments which are tangent to each other. The centerline and surfaces of each segment have constant change of angle with path distance. The stacking line for the blade elements can be leaned in both the axial and tangential directions. The output of the computer program gives coordinates for fabrication and properties for aeroelastic analysis for planar blade sections. These coordinates and properties are obtained by interpolation across conical blade elements. The program is structured to be coupled with an aerodynamic design program.
File Size	9509834
Page Count	226
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19740009588
Archival Resource Key	ark:/13960/t7vm9199w
Language	English
Publisher Date	1974-02-01
Access Restriction	Open
Subject Keyword	Aerodynamics Compressor Rotors Axial Flow Turbines Numerical Analysis Turbine Blades Engine Design Turbomachinery Aerodynamic Characteristics 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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