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Axial-flow fan and compressor blade design data at 52.5 ̊stagger and further verification of cascade data by rotor tests

Author: Seymour M Bogdonoff; Eugene E Hess; United States. National Advisory Committee for Aeronautics.; Langley Aeronautical Laboratory.
Publisher: Washington, D.C. : National Advisory Committee for Aeronautics, 1947.
Series: Technical note (United States. National Advisory Committee for Aeronautics), no. 1271.
Edition/Format:   Print book : National government publication : EnglishView all editions and formats
Database:WorldCat
Summary:
Previous tests of blower-blade sections have been extended by a series of tests at 52.5 degrees stagger. The results of these tests have been combined with the earlier test results and are presented in new blade design charts which supersede those previously presented. An investigation in a test blower over a range of stagger from 44 degrees to 65 degrees has shown that for blades at a solidity of 1.0, the  Read more...
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Details

Material Type: Government publication, National government publication
Document Type: Book
All Authors / Contributors: Seymour M Bogdonoff; Eugene E Hess; United States. National Advisory Committee for Aeronautics.; Langley Aeronautical Laboratory.
OCLC Number: 38204647
Notes: "April 1947."
Cover title.
NACA TN No. 1271.
Description: 4, [17] p. : ill. ; 27 cm.
Series Title: Technical note (United States. National Advisory Committee for Aeronautics), no. 1271.
Responsibility: Seymour M. Bogdonoff and Eugene E. Hess.

Abstract:

Previous tests of blower-blade sections have been extended by a series of tests at 52.5 degrees stagger. The results of these tests have been combined with the earlier test results and are presented in new blade design charts which supersede those previously presented. An investigation in a test blower over a range of stagger from 44 degrees to 65 degrees has shown that for blades at a solidity of 1.0, the two-dimensional cascade data predict the turning angle to within 1/2 degree.

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